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Reference PA1716
Covering dates 20th Century
Held by Coventry Archives
Creators Rolls Royce Heritage Trust

Contents:
Large collection of files, photographs, plans, reports etc. relating mostly to aero engines and rockets, but with some information relating to cars. Deposited by Rolls-Royce Heritage Trust. The object of the Rolls-Royce Heritage Trust is to act as the focal point for maintaining and promoting all aspects of the engineering heritage of the Company and of its corporate predecessors



Armstrong Siddeley/Bristol Siddeley & Rolls-Royce Gas Turbines from 1942 to 2001  PA1716/5  [n.d.]

Proteus Engine  PA1716/5/10  [n.d.]

Proteus Aero  PA1716/5/10/1  [n.d.]

Proteus Engine and Proteus Power Plant Arrangement Drawings  PA1716/5/10/1/1  1952 - 1963

5 Items

Proteus Strain Guage Reports  PA1716/5/10/1/2  1951 - 1968

31 Items

Maintenance Manual: Proteus 750/760 Series Power Unit  PA1716/5/10/1/3  5 October 1965

1 Item

Proteus Metallurgical and Chemical Laboratory Reports  PA1716/5/10/1/4  1963 - 1966

1 Item

Proteus Pressure Test Reports  PA1716/5/10/1/5  1951 - 1961

1 Item

Proteus Test Bed Reports  PA1716/5/10/1/6  April 1967 - July 1967

7 Items

General Description: 2 Megawatt Turbo-Generator  PA1716/5/10/1/7  November 1959

1 Item

Maintenance Manual: Bistrol Siddeley 1200 KW Trailer Set, Volume One  PA1716/5/10/1/8  c. 1960s

1 Item

Proteus Vibration Tests, SV.67  PA1716/5/10/1/9  1949 - 1956

1 Item

General Description: Bristol Proteus 765 Engine  PA1716/5/10/1/10  February 1958

1 Item

General Description: Proteus B.Pt.4 Engine  PA1716/5/10/1/11  March 1958

1 Item

Preliminary Performance Estimates for Proteus 770  PA1716/5/10/1/12  October 1958

1 Item

Installation Data: Proteus 755 Engine  PA1716/5/10/1/13  November 1955

1 Item

General Description: Proteus 770 Turboprop Engine  PA1716/5/10/1/14  April 1959

1 Item

Proteus 761 Engine Log Book  PA1716/5/10/1/15  1958

1 Item

Maintenance Manual: 3 MEgawatt Turbo-Generator  PA1716/5/10/1/16  September 1960

1 Item

Proteus Impeller Fatigue Tests  PA1716/5/10/1/17  1964 - 1967

29 Items

Proteus Stress Reports on Static Tests  PA1716/5/10/1/18  1950 - 1966

25 Items

Proteus Reports on Bearings for Starter Drive  PA1716/5/10/1/19  1952 - 1963

1 Item

Proteus Reports on Turbine Stators  PA1716/5/10/1/20  1965 - 1968

10 Items

Arrangement drawings: Proteus 255, 755-758, 761, 762, 765 and 766 Engines  PA1716/5/10/1/21  10 March 1960

1 Item

Sectional arrangement drawings: Proteus 700 Series  PA1716/5/10/1/22  1950s

1 Item

Arrangement drawings: Proteus 1200 Series  PA1716/5/10/1/23  1960s

2 Items

Proteus Industrial & Marine  PA1716/5/10/2  [n.d.]

Press cuttings from Home and Overseas on the Bristol Siddeley 3 MW sets at Princeton, Lynton, Porlock and St. Austell  PA1716/5/10/2/1  1950s - 1960s

1 Item

Rolls-Royce Gas Turbines for Small Craft  PA1716/5/10/2/2  June 1979

1 Item

The Marine Application of Lightweight Gas Turbines, A Talk Given at the Danish Institute of Engineering on 5 November 1959  PA1716/5/10/2/3  February 1960

1 Item

General Description: Marine Proteus Mark 1270, Gas Turbine Engine  PA1716/5/10/2/4  June 1959

1 Item

File of press cuttings regarding the Proteus portable generator  PA1716/5/10/2/5  1960s

1 Item

Article: 'Engineering News', Bristol Siddeley exhibit three gas turbines at texas conference  PA1716/5/10/2/6  8 March 1962

1 Item

Volume of press cuttings regarding the Proteus mobile power station  PA1716/5/10/2/7  1960s

1 Item

Bristol Siddeley Press Release: First Mobile Turbo-Generator for Steel Works  PA1716/5/10/2/8  7 May 1963 - 13 January 1965

1 Item

Bristol Siddeley Engines Limited: Proteus PT.1277 Industrial gas turbine  PA1716/5/10/2/9  June 1960

1 Item

Contents:
Manual TBD.23. The PT.1277 is a member of the Proteus family of engines of industrial and marine engines

Bristol Siddeley Engines Limited: Transportable 3 megawatt generating set. PT.1277 Proteus gas turbine  PA1716/5/10/2/10  November 1960

1 Item

Contents:
Manual TBD.19. The pack incorporates the Bristol Siddeley PT.1277 gas turbine. This is basically the well-tried Proteus engine, which powers the Britannia aircraft, and the Royal Navy's Brave Class fast patrol boats. The industrial engine, used for regular peak-lopping, is designed for an overhaul life of 10 years, and where long periods at continuous running are required, for example, as the sole source of supply in remote areas, the set can be provided at a reduced output rating

Proteus breakdown: Commercial - In Confidence  PA1716/5/10/2/11  c. 1940s

1 Item

Contents:
Includes attached article from 'Flight': Bristol Proteus, A High-compression Turbopulp for Wing Mounting (18 August 1949)

Proteus History  PA1716/5/10/2/12  c. 1950s

1 Item

Fuel System Diagrams  PA1716/5/10/2/13  December 1953

3pp

Proteus Propellor Turbine Engine for Marine Applications  PA1716/5/10/2/14  May 1955

1 Item

Proteus 755 Engine, Propeller Turbine Installation  PA1716/5/10/2/15  November 1955

1 Item

Hovercraft: newspaper cuttings and magazine articles  PA1716/5/10/2/16  1956 - 1964

8pp

Marine Proteus Engine: A paper read by B.G. Markham to the Society of Naval Architects and Marine Engineers in Washington  PA1716/5/10/2/17  January 1956

1 Item

Proteus Engine Instruction Diagrams: Amendment Copy  PA1716/5/10/2/18  June 1956

1 Item

Proteus 1250 Engine for Marine Application: Application Data  PA1716/5/10/2/19  15 August 1956

1 Item

Marine Proteus 1250 Gas Turbine Engine: Installation Data  PA1716/5/10/2/20  July 1957

1 Item

Notes concerning Proteus turbine disk  PA1716/5/10/2/21  18 March 1958 - 20 March 1958

3pp

Reports concerning Proteus 4 turbine temperature  PA1716/5/10/2/22  1958 - 1959

1 Item

Marine Proteus 1260 Gas Turbine Engine: Installation Data  PA1716/5/10/2/23  April 1958

1 Item

Bristol Marine Proteus 1260 Gas Turbine Engine: Technical Data  PA1716/5/10/2/24  June 1958

1 Item

Development of the Proteus 750 and 760 Series Engines  PA1716/5/10/2/25  June 1958

1 Item

Proteus Repair Schemes Register  PA1716/5/10/2/26  October 1958 - September 1965

1 Item

Marine Proteus Mark 1270 Gas Turbine Engine: General Description  PA1716/5/10/2/27  June 1959

1 Item

2 Megawatt Turbo-Generator: Installation Data  PA1716/5/10/2/28  November 1959

1 Item

ASME Publication: Development and Sea Trials of Marine Proteus Engines for Brave Class Fast Patrol Boats  PA1716/5/10/2/29  c. 1959

1 Item

Brochure: Proteus Turbo Generator  PA1716/5/10/2/30  c. 1960s

2 Items

Contents:
Includes card 'The Marine Proteus, A Gas Turbine Marine Engine'

Proteus 255 Series Engine: Aero Engine School course notes  PA1716/5/10/2/31  c. 1960s

1 Item

The Proteus - Medivane Pump Unit  PA1716/5/10/2/32  c. 1960s

1 Item

Brochure: Bristol Siddeley 35/40 megawatt turbo generator  PA1716/5/10/2/33  c. 1960s

1 Item

Technical Specification: Proteus BS.PT. 10M/533, Marine Engines 1,000 RPM Output (Admiralty)  PA1716/5/10/2/34  c. 1960s

1 Item

The Bristol Proteus Marine Engine Test Plant  PA1716/5/10/2/35  c. 1960s

1 Item

Proteus 755 Series Engine: Aero Engine School course notes  PA1716/5/10/2/36  c. 1960s

1 Item

Marine Proteus Engine: Installation Data  PA1716/5/10/2/37  1960

1 Item

Handbook for Bristol Proteus 1250 Marine Gas Turbine, Brave Class Fast Patrol Boats  PA1716/5/10/2/38  c. January 1960

1 Item

Diagrams of generator installations  PA1716/5/10/2/39  23 March 1960

1 Item

Brochure: Marine Proteus, a gas turbine marine engine  PA1716/5/10/2/40  April 1960

1 Item

Marine Proteus 1270 Series: General Description  PA1716/5/10/2/41  May 1960

1 Item

Bristol Siddeley Proteus Marine and Industrial Engines: General Data  PA1716/5/10/2/42  May 1960

1 Item

Marine Proteus 1270 Series: General Description  PA1716/5/10/2/43  May 1960

1 Item

3 Megawatt Turbo-generator: Maintenance Manual  PA1716/5/10/2/44  September 1960

1 Item

Bristol Siddeley, Proteus Marine and Industrial Engines: General Data  PA1716/5/10/2/45  October 1960

1 Item

Marine Proteus 1260 Engine: Maintenance Manual  PA1716/5/10/2/46  December 1960

1 Item

Marine Proteus Engine: Installation Data  PA1716/5/10/2/47  March 1961

1 Item

Proteus description: presented to the Heritage Trust (Coventry Branch) by P.A. Round  PA1716/5/10/2/48  c. December 1986

1 Item

Proteus photographs  PA1716/5/10/2/49  16 June 1961 - 10 October 1966

10 Items

Brochure: Bristol Siddeley Marine Proteus  PA1716/5/10/2/50  December 1961

1 Item

Marine Proteus PT.1270 Series: Operation and Maintenance Manual  PA1716/5/10/2/51  January 1962

1 Item

3 Megawatt Turbo-generator: General Description  PA1716/5/10/2/52  January 1963

1 Item

Proteus Civil Engines and Accessories: Overhaul Modifications Schedule Reference Number 35  PA1716/5/10/2/53  May 1963

1 Item

Marine Proteus: General Description  PA1716/5/10/2/54  October 1963

1 Item

Diagrams concerning Proteus engines  PA1716/5/10/2/55  16 October 1963 - 1964

17 Items

An assessment of various types of heat exchanger suitable for use with the Proteus engine  PA1716/5/10/2/56  14 November 1963

1 Item

Newspaper articles concerning Proteus hydrofoils  PA1716/5/10/2/57  1963 - 1966

3pp

Proteus Engines Series 700: Installation Data  PA1716/5/10/2/58  c. January 1964

1 Item

Proteus Turbo Generator: Allegemeine Beschreibung  PA1716/5/10/2/59  March 1964

1 Item

Contents:
In German

Proteus Turbo Generator: General Description  PA1716/5/10/2/60  September 1964

1 Item

An Investigation of the Proteus Incorporating a Heat-Exchanger  PA1716/5/10/2/61  8 September 1964

1 Item

Brochure: Proteus turbogenerator  PA1716/5/10/2/62  October 1964

1 Item

Contents:
In Spanish

Brochure: Proteus Marine Gas Turbine  PA1716/5/10/2/63  January 1965

1 Item

Brochure: Bristol Siddeley supply the power  PA1716/5/10/2/64  February 1966

1 Item

Preliminary report on the satisfactory completion of 3000 hours continuous running of Proteus engine no.10016 in the admiralty test house at NGTE Pyestock  PA1716/5/10/2/65  27 September 1966

1 Item

Reports on Proteus turbine discs  PA1716/5/10/2/66  13 December 1966 - 1979

1 Item

Proteus Gas Turbine: Technical Specification  PA1716/5/10/2/67  March 1967

1 Item

Minutes of Air Registration Board meeting No.38 held at Coventry to discuss Proteus engines  PA1716/5/10/2/68  3 April 1967

1 Item

Marine Proteus engines: Service and maintenance  PA1716/5/10/2/69  28 July 1967

1 Item

Brochure: Proteus industrial power  PA1716/5/10/2/70  September 1967

1 Item

Brochure: Proteus marine power  PA1716/5/10/2/71  June 1969

1 Item

Proteus marine engines installation brochure: Part A, mandatory installation requirements  PA1716/5/10/2/72  January 1970

1 Item

Proteus Mk.255 engine and Proteus Mk.25501 engine change unit: Preservation and storage  PA1716/5/10/2/73  March 1970

1 Item

Brochure: Proteus gas turbine heavy maintenance  PA1716/5/10/2/74  February 1970

1 Item

Brochure: Marine Proteus gas turbine  PA1716/5/10/2/75  November 1971

1 Item

Report on modes of failure of cooled turbine rotor blades T.S.R. 546  PA1716/5/10/2/76  30 August 1973

1 Item

Report on Proteus 52M/554 - Acceleration Times T.S.R. 567  PA1716/5/10/2/77  5 November 1973

1 Item

Proteus test report PTR 220  PA1716/5/10/2/78  24 January 1974

1 Item

Leaflet: Rolls-Royce Proteus marine gas turbine  PA1716/5/10/2/79  March 1977

1 Item

Internal memorandum: Proteus Mk.780 engines, proposed overhaul life and component lives  PA1716/5/10/2/80  21 February 1975

1 Item

Proteus test report PTR 234, mobility survey of Proteus engines  PA1716/5/10/2/81  21 October 1976

1 Item

Repair note: Life limitation of turbine discs  PA1716/5/10/2/82  15 March 1977

1 Item

Rolls-Royce Marine Proteus Gas Turbine: General Description  PA1716/5/10/2/83  April 1980

1 Item

Stress Department reports concerning marine Proteus, mainly 755 in Britannia  PA1716/5/10/2/84  1955 - 1956

1 Item

General Description: Marine Proteus  PA1716/5/10/2/85  October 1963

1 Item

Proteus Propeller Turbine Engine for Marine Applications  PA1716/5/10/2/86  May 1955

1 Item

General Description: The Bristol Marine Proteus 1260 Gas Turbine Engine  PA1716/5/10/2/87  June 1958

1 Item

Marine Proteus 1282 Gas Turbine, Parts Catalogue MGT.82  PA1716/5/10/2/88  June 1958

1 Item

Technical Specification: Marine Proteus Gas Turbine  PA1716/5/10/2/89  September 1967

1 Item

General Description: Proteus 524 0 Gearbox  PA1716/5/10/2/90  1968

1 Item

Report No.P.T.R.114: Installation and Initial Running of Proteus Marine Engine No.10,016 in the Admiralty Test House at the National Gas Turbine Establishment at Pyestock  PA1716/5/10/2/91  21 April 1964

1 Item

Tender: Proteus Powered Industrial Plant  PA1716/5/10/2/92  8 September 1966

1 Item

Marine Proteus 1282 Gas Turbine, Parts Catalogue MGT.82  PA1716/5/10/2/93  May 1970

1 Item

Volume of newspaper cuttings concerning marine Proteus  PA1716/5/10/2/94  1968 - 1969

1 Item

Brochure: Marine Proteus Gas Turbine  PA1716/5/10/2/95  March 1974

1 Item

Brochure: Marine Gas Turbine  PA1716/5/10/2/96  January 1965

1 Item

Brochure: Marine Proteus, a gas turbine marine engine  PA1716/5/10/2/97  April 1960

1 Item

Proteus Master Test Schedule for Engine Acceptance Testing  PA1716/5/10/2/98  January 1974

1 Item

Proteus 3 Axial Compressor, Cooper Bessemer 14 Stage Version  PA1716/5/10/2/99  27 August 1969

1 Item

File of papers concerning Proteus Turbine Engines  PA1716/5/10/2/100  1954 - 1964

1 Item

Stress Reports: Britannia Vibration Tests, SV.70  PA1716/5/10/2/101  1954 - 1958

1 Item

Outside Erection Department: Master Log Book, 1 x 3 M.W. Turbo-Alternator Set  PA1716/5/10/2/102  December 1963

1 Item

Outside Erection Department: Master Log Book, 4 x 3 M.W. Generating Sets  PA1716/5/10/2/103  c. 1960s

1 Item

Marine Proteus and other power Proteus Vibration Tests, SV.83  PA1716/5/10/2/104  1955 - 1960

1 Item

Photographs of mobile 3 MW Gas Turbo Generator  PA1716/5/10/2/105  1960s

58 Items

Proteus Reports on Civil Aircraft Performance  PA1716/5/10/2/106  1964 - 1968

24 Items

File of photographs of M.W. mobile generator sets  PA1716/5/10/2/107  c. 1960s

2 Items

Proteus Engines Reports and Engine Stress Investigations  PA1716/5/10/3  1954 - 1957

1 file

Olympus Engine  PA1716/5/11  [n.d.]

Bristol Aeroplane Company, Bristol Aero Engines Ltd: Olympus aero engines maintenance manuals and performance reports  PA1716/5/11/1  1954 - 1963

Bristol Olympus engines Marks 101, 102 & 104 installation data  PA1716/5/11/1/1  11 March 1954

1 Item

Contents:
Olympus aero engine. Bristol Aero-engines Limited. A subsidiary of the Bristol Aeroplane Company Limited. Section 1: Engines T.2358 issue 8; Section 2: Engines T2358 issue 10

Olympus B.O1.21 turbojet engine  PA1716/5/11/1/2  1954 - 1960

2 Items

Bristol Aero-engines Limited: Olympus B.O1.6/21 engine advance performance folder  PA1716/5/11/1/2/1  c. 1954

1 Item

Contents:
Olympus aero engine. APF.35. The B.O1.21 engine is a development of the B.01.6 by the addition of an extra stage to the LP compressor. Full index of performance curves and calculations

Bristol Siddeley: Olympus B.O1.21 turbojet engine. Performance  PA1716/5/11/1/2/2  August 1960

1 Item

Contents:
Olympus aero engine. Ref: TC 222/2. The Bristol Siddeley Olmpus B.01.21 engine is a two-spool turbojet with a maximum rating of 20,000 lbs thrust and a maximum continuous rating of 17,700 lbs thrust. It combines the features of high thrust/weight ratio with low specific fuel consumption and is a development of the Olympus Mk.201 engine of 17,000 lbs thrust which was type-tested in May 1958 and is in full production for the Avro Vulcan Mk.B.2 aircraft

Curtis-Wright Bristol Aero-engines Limited: Olympus B.O1.14R turbojet engine  PA1716/5/11/1/3  January 1958

1 Item

Contents:
Olympus aero engine. TC.219. The Bristol Olympus B.O1.14R engine is a military version of the Olympus 551 engine, giving, under sea-level static conditions, 13,250 lbs of dry thrust or 23,050 lbs with reheat on. if required for take-off the dry thrust can be increaed to 15,450 lbs. The Bristol Olympus 551 is an engine which is subject of a licence agreement between this company and the Curtis-Wright Corporation, Woodridge, New Jersey - the engine being marketed in the USA as the Curtis-Wright Zephyr. The civil form from the engine has been offered to the world's airlines as an engine for medium range subsonic jet transports. The performance curves (as listed in Appendix A) 10 sheets and curve B.124012A. Appendix B (T.2280.A and curve B.68015.B)

Bristol Aero-engines Limited: Olympus 101 turbojet engine. Advance performance folder with curves  PA1716/5/11/1/4  November 1956

1 Item

Contents:
Olympus aero engine. APF.48. This performance folder is intended to be used in conjunction with the latest issue of MoS Technical Certificate BLT/5 and subsequent amendments, which should be consulted for operating limits on LP compressor rpm, HP compressor rpm, and jet pipe temperature. The accompaning curves are based on the measured flight performance of development engines; Appendix A details the correction to be applied to bring the folder into line with production engines. Appendix B explains the method of using the non-dimensional curves. In using the folder 100% LP rpm should be taken as 6,500 rpm

Bristol Aero-Engines Limited: BS Olympus Mk.104 for the Handley Page Victor Mk.1  PA1716/5/11/1/5  November 1958

1 Item

Contents:
Olympus aero engine. Restricted. TS.1324. Bristol Aero-Engines Limited. The Bristol Olympus Mk.104 is a two-spool turbojet with a maximum rating of 13,000 lb thrust. It has a high thrust/weight ratio and a low specific fuel consumption

Bristol Siddeley Engines Limited Projects Department: Olympus BS.O1.22R turbojet engine. Performance data  PA1716/5/11/1/6  July 1959

1 Item

Contents:
Olympus aero engine. PS.70/2. The Olympus BS.O1 22R is derived directly from the Olympus BS.10.15 by the addition of a zero-stage to the LP compressor. The engine is equipped with a fully variable reheat system which is being developed in conjunction with the Solar Aircraft Company of San Diego, USA. The performance in this brochure has been estimated by methods agreed with the National Gas Turbine Establishment and the Ministry of Aviation, and all data quoted are for an average engine

Bristol Siddeley Engines Limited: BS Olympus Mk.104 turbojet engine. Performance data  PA1716/5/11/1/7  January 1960

1 Item

Contents:
Olympus aero engine. TRH.38. The BS Olympus Mk.104 engine is a two-spool turbojet with a maximum rating of 13,000 lb thrust. It has a high thrust/weight ratio and a low specific fuel consumption. Many thousands of hours of flying under service and development conditions have proved the soundness of the two-spool compressor principle which provides the engine with exceptional flexibility and ease of control in spite of the high pressure ratio

Bristol Siddeley Engines Limited, Aero development Coventry: Summary of the development history of the Olympus 100 series engines  PA1716/5/11/1/8  10 April 1963

1 Item

Contents:
Olympus aero engine. AD(C)4. The Olympus, the first twin-spool engine to be designed, ran for the first time in 1950. It has an excellent specific fuel consumption, good handling characteristics, and ease of accessibility of major components. The original engine, now the Olympus 100 series,was developed for the Avro Vulcan bomber Mk.1 aircraft; later derivations (200/300 series) now power the Vulcan B Mk.2 and further members of the family, 320 and 593 are being developed for more advanced supersonic aircraft. Some versions (200 series) also have industrial and marine application. Production of the Mk.101 started in 1954, followed by more powerful Mk.102 and Mk.104 engines. Production ceased in 1959

Bristol Aero-Engines Limited, Publicity brochure: Olympus turbojet engine  PA1716/5/11/1/9  August 1956

1 Item

Contents:
Olympus aero engine. B Olympus 3-1. Bristol Aero-engines Limited. A subsidiary of the Bristol Aeroplane Company, Filton Bristol. After an official type test in November 1955, the Olympus 102 was approved for service at 12,000 lbs thrust without reheat; security restrictions do not permit the release of later information. In 1953 an earlier, less powerful version, installed in an English Electric Canberra MK.2, had raised the world altitude record to 63,668 ft in practical proof of the claim that the Olympus produced more power at higher altitude than any other engine. On August 29 1955 the same aircraft, with later type Olympus engines, improved its on record to 65,890 ft. In spite of this remarkable performance the Olympus is also one of the most economical turbojet in the world

Bristol Aero-Engines Limited: Drawing TP.2746: Fuel system diagram Olympus 101 and 104 engines  PA1716/5/11/1/10  November 1955 - February 1958

2 Items

Contents:
Olympus aero engine. Bristol Aero-Engines Ltd; Technical Publications Department, Filton, Bristol

Bristol Gas Turbines: Olympus stress reports & calculations for all models  PA1716/5/11/2  1948 - 1981

Contents:
Stress calculations and relevant curves

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus low pressure BE.10. Proposed new shape root fixing. Group II (.250 pitch)  PA1716/5/11/2/1  6 December 1948

1 Item

Contents:
Ref: 434c.1/4. 10-page hand-written report (in pencil) of blade calculations by KER. Tabulated summary of blade stresses for roots of varying pitches

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus clamping plates for low pressure compressor  PA1716/5/11/2/2  21 December 1948

1 Item

Contents:
Ref: 4343/5. Hand-written (in pencil) report and calculations by ENC. These plates should be as designed that when rotating, they exert a net axial thrust which balances the gas loading on the rotor blades. This axial thrust is brought about by the provision of a suitable cone angle and rim on one of the plates. In this case the gas loading falls back on to the front plate and so this plate must be designed to balance the load, the [ ] of which is 5500 lbs under ICHN conditions. Since the clamping load is solely dependent on speed it is evident that this load can only be correct for one set of atmospheric conditions. Under any other set the gas load will either be greater or less than the clamping load and this out-of -balance load will tend to deflect the plates. The plates must therefore have sufficient stiffness to ensure that this out-of-balance load does not produce a large deflection with corresponding shift of blades. Additional effects to be considered are gyroscopic pression and possible pressure drop acoss the plates. Graph 1: Rotational stresses in clamping plate (2nd design). Graph 2: Radial displacement of plate and labyrinth ring (2nd design)

Bristol Aero Engines Limited: Bristol Olympus Mk.200 installation data  PA1716/5/11/2/3  29 December 1948

1 Item

Contents:
Ref: 434C.1/4. Hand-written (in pencil) by KER. Shows the root fixings in addition to the binding stress in the lobes. Page 2: tabulation of blade root stresses

Bristol Gas Turbines: Olympus 100 series stress investigation. Low pressure Olympus compressor. Redesign of clamping plates  PA1716/5/11/2/4  22 March 1949

1 Item

Contents:
Ref: 4343/5. 16 page hand-written report (in pencil) with drawings of components and a slope curve for disc subjected to a rim load of 100lbs. by KER

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus low pressure compressor. Spacing ring location of compressor blades  PA1716/5/11/2/5  24 January 1949

1 Item

Contents:
Ref: 434C.1/4. Hand-written (in pencil) 5-page report with diagrams of components and calculations by KER

Bristol Gas Turbines: Olympus 100 series stress investigation. LP compressor rotor, Scheme OLS.125 (Issue A.)  PA1716/5/11/2/6  25 January 1949

1 Item

Contents:
Ref: 4343/3 from Stress Office. Design memorandum GDM/BE/10/6. The rotor disc profiles should be in accordance with a previous recommandation (see GDM/BE/10/1 15 september 1948)

Bristol Gas Turbines: Olympus stress investigation. LP compressor rotor, Scheme OLS.125 (Issue A.)  PA1716/5/11/2/7  25 January 1949

1 Item

Contents:
Different content to PA1716/5/11/2/6 although references are the same. Stress office Ref: 434c.1/3. 434SR Design memorandum GDM/BE/10/6. The ending clamping plates conform with our earlier suggestions. 1 Drawing of clamping plate front Mat=S.II drawing of clamping plate front. Mat=S.II drawing of clamping plate rear

Bristol Gas Turbines: Olympus 100 series stress investigation Olympus compressor LP compressor driving shaft, Scheme OLS.133  PA1716/5/11/2/8  9 April 1949

1 Item

Contents:
Ref: 4343/3 Hand-written (in pencil) 10-page report with drawings of components and stress calculations by RD Fuller

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus LP compressor drive shaft  PA1716/5/11/2/9  31 May 1949

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Ref: 434C.1/3. 2-page report

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus front section compressor. General considerations of driving dowels and clamping bolts  PA1716/5/11/2/10  10 October 1950

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434c.1/3. 10-page report of calculations by KER

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus tightening extension for front section compressor bolts  PA1716/5/11/2/11  6 October 1950

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Ref:434c.1/3. Design memorandum GDM/BE.10/42

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus front section compressor. Fabricated rotor blade fixing  PA1716/5/11/2/12  24 January 1950

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Ref: 4343/4. design memo GDM/BE.10/30. Steel rotor blades for hollow steel blades. KWF/EN

Bristol Gas Turbines: Olympus 100 series stress investigation. Olympus front section compressor. Fabricated rotor blade fixing  PA1716/5/11/2/13  2 February 1950

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Ref: 434c1/4. Steel rotor blades for hollow steel blades. Drawings OLS.245 & OLS.246 KWF/EN

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus LP compressor driving shaft  PA1716/5/11/2/14  22 January 1951 - 26 February 1951

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Ref: 434c.1/3. Compressor driving shafts B.25541 & B.45334. Calculations 22 January 1951. Memo 26 February 1951

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus Front Section Compressor Driving Shaft B.51025  PA1716/5/11/2/15  11 July 1951

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Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus LP low pressure compressor. Group 1 Stage 1 Rotor blade  PA1716/5/11/2/16  31 January 1950

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Ref: 434c.1/4. Root fixing with hollow steel blades. sch/EMV/E to M/s 1123 and OLS.245 WM Owen. 7-page report, calculations and drawings of precision cast root to M/s1123

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus LP compressor driving shaft B.50214  PA1716/5/11/2/17  17 January 1951

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Ref: 434c.1/3. 3-page report and calculations by KER

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus front section compressor driving shaft B.50214  PA1716/5/11/2/18  19 July 1951

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Ref: 434c.1/3. report and drawing B.50214 attached

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus Low Pressure Compressor  PA1716/5/11/2/19  c. 1951

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Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus Low Pressure Compressor Rotor Blades  PA1716/5/11/2/20  c. 1951

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Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Drawing B.97852 of Olympus front compressor driving shaft  PA1716/5/11/2/21  23 May 1955

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Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Drawing 3rd angle projection B.70030 of Olympus front compressor driving shaft  PA1716/5/11/2/22  30 May 1952

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Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Low Pressure Compressor Rotor  PA1716/5/11/2/23  18 February 1953

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Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Computation of CG of rotor blades  PA1716/5/11/2/24  c. 1951

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Ref: 434c.1/4. 7-page (in pencil) report with calculations

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus 1/2 LP compressor rotor clamping bolts. Tightening extensions for waisted bolts for increased length bolts for use with O-stage compressor  PA1716/5/11/2/25  10 December 1953

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Ref: 434c.1/3. Calculations attached

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus 1/2 LP compressor. Tightening extensions for rotor clamping bolts  PA1716/5/11/2/26  15 December 1953

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Ref:434c.1/3. Report with tabulated type of bolt and tightening extension details by KR Chamberlain

Bristol Gas Turbines, Olympus Mk.101 & Mk.1022 stress investigation: Olympus LP compressor rotor clamping bolts  PA1716/5/11/2/27  23 February 1956

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Ref: 434c.1/3. Tightening extensions for new bolts of S.106 material compound with the existing bolts of Bace 140 material. Scheme drawing used OLS.313. Previous calculation 4343/3 10 December 1953; 4342SR/10. Page 6 graph: Tightening extension - .001 ins

Bristol Gas Turbines: Olympus Mk.101 & Mk.1022 stress investigation. Olympus Mk.104 LP rotor  PA1716/5/11/2/28  c. 1950

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One page tabulated performance of Olympus Mk.104 rotor at sea level; M 0.84, 240Kts, 350Kts; Max rating etc.

Bristol Gas Turbines: Olympus Mk.100 stress investigation. Report on Olympus Normal sortie ISA conditions  PA1716/5/11/2/29  c. 1950

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Contents:
Three pages of calculation. Final page: Alternative breakdown of a low level sortie at ISA

Bristol Gas Turbines: Olympus Mk.100 stress investigation. Low pressure compressor. General investigation into rotor assembly  PA1716/5/11/2/30  29 December 1948

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Ref: 4343/6. We will consider now the few outstanding points which have not been covered in previous calculations: 1 Corridor rim bearing length between blade platform and spacing ring, 2 Corridor binding between spacing rings. 3 Corridor shear in main driving shaft.KER

Bristol Gas Turbines: Olympus 100 series stress investigation. Low pressure compressor. End clamping plates  PA1716/5/11/2/31  7 April 1949

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Ref: 4343/5. Design memo GDM/BE.10/6. Alternative designs for low pressure compressor clamping plates. 3-page report with drawings Mat.SII, and Sixth stage disc replacing existing Dural disc and rear clamping plate

Bristol Gas Turbines: Olympus 100 series stress investigation. LP compressor spacing ring modification  PA1716/5/11/2/32  21 June 1950

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Ref: 4343/6.TC Greaves. An appropriate investigation into the suitability of a modified spacing ring locating radically on the disc and axially on the back platforms

Bristol Gas Turbines: Olympus Mk.2 series stress investigation. LP compressor rotor. General stressing of the rotor assembly  PA1716/5/11/2/33  2 February 1951

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Ref: 4343SR/17. RE Jenkins. Schemes or drawings used: OLS.412.37-page report with calculations and graphs: 37 Olympus Mk.2 LP compressor 1st & 2nd stage discs; 38Mk.2 LP compressor rotor 1st & 2nd stage discs; 39 Mk.2 LP compressor rotor 3rd & 4th stage discs. Ref: 4341c.1SR/6. Last page: Olympus Mk.1 spacing rings. Proposal to slot flange to receive firm radial location

Bristol Gas Turbines: Olympus 1/2A stress investigation. Stiffness test on LP compressor rotor shaft  PA1716/5/11/2/34  5 December 1951 - 11 December 1951

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Ref: 4343.SR/8. KB Chamberlain. report and graph. Graph GR.2755: Stiffness test LP compressor rotor shaft

Bristol Gas Turbines: Olympus Mk.3 stress investigation. The stresses in the compressor driving and rotor centres  PA1716/5/11/2/35  18 February 1952

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Ref: 4343/10.Olympus Mk.3 LP compressor rotor shaft and rotor centre. Drawing used 035 116 and 144. Page 1,2: Calculations. Pages 3-5: Loading tabulations. Report by RE Jenkind

Bristol Gas Turbines: Olympus Mk.1/2c stress investigation. Design of front rotor flange and calculation of axial deflections of rotor assembly  PA1716/5/11/2/36  14 October 1952

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Ref: 4343/5. Olympus Mk.1/2c LP compressor rotor assembly. Pages 1-8: Clamping load due to front flange. Pages 9-11: Clamping load due to rear flange. Pages 12-17: Deflection of rotor assembly. Page 18: Bearing pressure on spacing rings. Report by JA Taylor

Bristol Gas Turbines: Olympus Mk.1/2c (101) stress investigation. A revised design of front clamping plate, and an investigation into its stiffness and stress distributions  PA1716/5/11/2/37  December 1952

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Ref: 4343SR/5. Olympus Mk.1/2c (101)ompressor (LP) front rotor flange. Drawing OLS 1317. This scheme incorporates the change to MS 1503. Pages 1-5: Calculations of clamping force. Pages 6-9:Stiffness of flange. Page 10: Stress distribution when deflected. Page 11: Overall rotor deflection. NB: Refer to MS 1503. Report byRE Jenkins

Bristol Gas Turbines: Olympus Mk.1/2c stress investigation. Rotor blade tip clearances (LP)  PA1716/5/11/2/38  7 January 1953

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Ref: 434C1/12. Olypmus Mk.1/2c LP compressor rotor. Data used TED 38 (6894/3). Previous calculations 4353/4 and 4363/11. Report by DJ Fortune

Bristol Gas Turbines: Olympus Mk.101 stress investigation: Low pressure compressor rotor assembly  PA1716/5/11/2/39  26 January 1954

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Ref: 434C1/12. Memo: Experimental Department Defect report 145/54. Defect: Loss of 'nip' between the rotor flange front B.89455 and the last stage blades on engine rebuild. Action taken in shops: On most of the development a concession has been obtained to restore the 'nips' by removing metal up to a maximum of 0.10 from the first stage disc abutment face on the flange

Bristol Gas Turbines: Olympus stress investigation: Letter from Curtis-Wright Corporation to AF Elliott; requesting stress information to check their results in relation to fir tree roots  PA1716/5/11/2/40  3 June 1954 - 9 June 1954

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Ref: 434C1/5. AF Elliot 'Could you please furnish us the following centrifugal stresses based on front and rear rotor speeds of 6150 and 7750 rpm, or as close to these speeds as you have calculated. Memo attached 434c1/5 9 June 1954

Bristol Gas Turbines: Olympus stress investigation: Memo fromStress department to No.4 Shop. Design suggestion No.618  PA1716/5/11/2/41  16 December 1953

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Ref: 434C1/1 and 434C2/1. Regarding the proposal to fit an adjusting washer under the rotor flanges (front) of the HP and LP compressor rotors we find that reducing the hub thickness of these parts by 0.50', required to accommodate this washer, leads to high stresses in the rotor and flanges

Bristol Gas Turbines: Olympus stress investigation: Memo from Stress department to No.4 Shop, to AF Elliott. Information required by Curtis-Wright  PA1716/5/11/2/42  17 June 1954

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Ref: 434c1/5. One page reply: Disc and rotor flange centrifugal stresses; set out in tabulated format

Bristol Gas Turbines, Olympus Mk.104 stress investigation: The stresses in the diaphragm and rotor flange associated with the air heated zones stage rotor blade scheme  PA1716/5/11/2/43  12 November 1956

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Ref: 434c1SR/5. Olympus Mk.104 LP compressor end flange and casing. Scheme/drawing used OLS 3750. Previous calculations 4343SR/5 December 1952. Report by RE Jenkins

Bristol Siddeley Engines Limited: Olympus Mk.104 stress investigation, Olympus 104 LP shaft torques  PA1716/5/11/2/44  18 December 1964

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Ref: 434c1/13. Internal memo: One page tabulated report by N Essex

Bristol Siddeley Engines Limited: Olympus Mk.104 Vulcan stress investigation: Memo re Olympus 104 low level operation  PA1716/5/11/2/45  23 November 1964

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PFG/RCP/8549 from RC Plumb. I should like to review again the possibility of flying the Olympus 104 in low level role for training, particularly in respect of compressor blade vibration

Bristol Siddeley Engines Limited: Olympus Mk.104 stress investigation: Shear stress in shaft (180,000 lb torque)  PA1716/5/11/2/46  7 December 1964

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Ref: 434c1/13. Scheme/drawing used B.97852 hand-written report with a diagram of torque range and calculations

Bristol Siddeley Engines Limited: Olympus Mk.104 Vulcan stress investigation: Component test schedule  PA1716/5/11/2/47  4 January 1965

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Contents:
Ref: 434c1/13. LP shaft and couplings when used in a low level training role

Bristol Siddeley Engines Limited. Olympus Mk.104 Vulcan stress investigation: Secret internal memo. Use of Olympus 104s in Vulcan for low level role training  PA1716/5/11/2/48  5 January 1965

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Ref: 434c1/13. The pop-up manoeuver associated with the low level role involves several cycles at torque higher than normal TC. A review was therefore made of the stresses in both LP and HP couplings. Tables 1 and 2 give tabulated results of tests

Bristol Siddeley Engines Limited: Olympus 104 stress investigation - LP compressor rear flange  PA1716/5/11/2/49  c. 1965

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Ref: 434c1/5. Rear flange with labyrinth passage removed OLS.1021. Bearing pressure against disc face. Graph and tabulated stresses. Olympus 104 de-iced zerostage rotor blade scheme OLS.3750

Bristol Siddeley Engines Limited: Olympus 1/2c stress investigation - LP compressor rear flange  PA1716/5/11/2/50  c. 1965

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Ref: 4343/5. Rear clamping plate. General consideration of rear clamping plates. R Humpridge

Bristol Siddeley Engines Limited: Olympus Mk.3 stress investigation - LP compressor rotor  PA1716/5/11/2/51  c. 1965

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Ref: 434c1SR/9. Disc, bolts and spacing rings; schemes/drawings used 03S. Pages 1-2: Calculations of disc loadings. Pages 3-7: Disc profiles. Pages 8-12: Graphs. Pages 13-15: Possible design of 1st disc in steel. Pages 16-21: Reactive forces of cored discs. Pages 22-25 Main rotor bolts. Pages 26-29: Spacing rings. Page 30: Generator drive coupling

Bristol Siddeley Engines Limited: Olympus 1/2B stress investigation - LP compressor front rotor drive OLS.729  PA1716/5/11/2/52  c. 1965

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Ref: 4343c/3. Drawing and calculations of LP compressor front rotor centre

Bristol Gas Turbines: Whirling of Olympus research compressor (RL.10229)  PA1716/5/11/2/53  5 September 1949

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Ref: 623D/7. Bristol Gas Turbines, Bristol Aeroplane Company. 8 pages of tabulated calculations

Bristol Gas Turbines: BE.10 low pressure research compressor. Estimates of weights and moments of inertia  PA1716/5/11/2/54  c. 1949

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Ref: 623D/7. Bristol Gas Turbines, Bristol Aeroplane Company. 7 pages of calculations

Bristol Gas Turbines: 5 Olympus Gneral arrangements  PA1716/5/11/2/55  1949 - 1952

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Ref: 623D/7. Traced 29 October 1951. 1 B.59350 Olympus 1/2 (Bristol cannular conbustion chambers)

Bristol Gas Turbines: Olympus turbine test rig. Whirling speeds  PA1716/5/11/2/56  4 July 1949

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Ref: 623D/7. Bristol Gas Turbines, Bristol Aeroplane Company. 11 pages of calculations with drawing

Bristol Aeroplane Company internal memo from Stress Office: Olympus 502, critical speeds  PA1716/5/11/2/57  26 June 1950

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Ref: 623D/7.We have today been asked to quote the critical speeds to avoid when operating Olympus and we give below the anticipated critical speeds based on calculations

Bristol Aeroplane Company internal memo: Olympus 502, HP shaft  PA1716/5/11/2/58  1 November 1950

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Ref: 623D/7. Confirming our conversation during the incremental running of Olympus 502 on the 1st November, it was very noticeable that the metal detector indicated the presence of metal between 7,100 and 7,300 hp rpm in appreciable quantities, but at other speeds it gave no appreciable indication of metal

Bristol Aeroplane Company Olympus stress calculations: Canberra Olympus gearbox drive shaft SKA.2476  PA1716/5/11/2/59  15 August 1951

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Ref: 623D/7. 3 pages of drawings and calculations

Bristol Aeroplane Company Stress Department: Reports  PA1716/5/11/2/60  1952

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Report re. strain gauging of Olympus blades  PA1716/5/11/2/60/1  2 May 1952

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Ref: 623D/7. The recent failure of 1st stage turbine and also LP and HP compressor rotor blades have once again emphasised the desirability of a train gauging under normal operational conditions in the engine

Extract from Minutes of Mech.Eng Sub.Com of the GTCC 26 October 1950  PA1716/5/11/2/60/2  2 May 1952

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Ref: 623D/7. 1 Energy transmission through which from blade to blade coupling effects very light, 80% if adjacent blades accurately turned

Stress calculations: Report re. Olympus compressor and turbine blade failures  PA1716/5/11/2/60/3  19 November 1952

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Ref: 623D/7. On Olympus 511 on 16 November 1952, two adjacent 8th stage HP compressor rotor blades failed in fatigue at the root at the base of the blade section and one HP turbine blade was cracked from the trailing edge. Inspection, however, is not complete and additional cracks may be found. Running time of all the blades was 57 hours 23 minutes. The failure appeared to be fatigue failure starting 1.6'radially inwards from outside of the blade shroud at the trailing edge. This is an incidental position to that of two previous failures, namely 505 and 501. The blades have run 43 hours 1 minute unwelded on acceptable and flight tests in Canberra and 14 hours 22 minutes, welded on acceptance and flight test in Canberra, so that there is a possibility that the failure was initiated before welding

Bristol Aeroplane Company Olympus stress calculations: Memo to Stress office from Component development Department west Works - Routine vibration measurements of Olympus engines  PA1716/5/11/2/61  20 November 1952

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Ref: 623D/7

Bristol Aeroplane Company Olympus stress calculations: Olympus III modifications to HP system  PA1716/5/11/2/62  30 May 1951

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Ref: 623D/6. KCF 4 page report and calculations

Bristol Aeroplane Company Olympus stress calculations: Olympus III with BE.21 shafting  PA1716/5/11/2/63  5 March 1952

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Ref: 623D/6. FH. 27 pages of drawings and calculations

Bristol Aeroplane Company Olympus stress calculations: Olympus Mk.1/2 & III whirling speeds  PA1716/5/11/2/64  c. 1952

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Ref: 623D/6. 9 pages of calculations

Bristol Aeroplane Company Olympus stress calculations: Olympus IV whirling speeds of HP rotor  PA1716/5/11/2/65  c. 1952

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Ref: 623D/6. 9 pages of calculations

Bristol Aeroplane Company Olympus stress calculations: Olympus III (No.6 bearing omitted) calculation of whirling speeds  PA1716/5/11/2/66  21 April 1952

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Ref: 623D/6. 11 pages of drawings and calculations

Bristol Aeroplane Company Olympus stress calculations: Olympus MK.3 modification to whirling speed HP shaft shortened by 3.4'  PA1716/5/11/2/67  c. 1952

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Ref: 623D/6. 5 pages of calculations and drawings

Bristol Aeroplane Company Olympus stress calculations: Olympus III whirling speed of HP shafting  PA1716/5/11/2/68  22 January 1951

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Ref: 623D/6. 13 pages of calculations

Bristol Aeroplane Company Olympus stress calculations: Second interim report on spinning tests carried out on B.0L.4 HP compressor rotor  PA1716/5/11/2/69  17 December 1953

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Ref: 623D/6. Report No.T.521/53. Issued by Component Development Department Aero Engine Division Bristol Aeroplane Company Limited. In continuity of the tests already conducted on the B.0L.4 HP compressor rotor up to a maximum speed of 8,300 rpm ie 5% overspeed (see CDD Report No.513/53); it was necessary, in order to complete the specified schedule, to carry out further tests on the rotor up to a maximum speed of 8,690 rpm (10% overspeed), and hold the rotor at this speed for a period of five minutes

Bristol Aeroplane Company Olympus stress calculations: Olympus 4 HP compressor rotor whirling speeds  PA1716/5/11/2/70  19 May 1954

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Ref: 623D/6. 9 page report and calculations with Stress Graph 4346 SR/8 (GR.3416)

Bristol Aeroplane Company Olympus stress calculations: Olympus Mk.101 drive shaft for Sunstrand constant speed unit  PA1716/5/11/2/71  6 September 1954

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Ref: 623D/7. 8 pages of calculations with drawing of Olympus Mk.101 Sunstrand constant speed unit

Bristol Aeroplane Company Olympus stress calculations. Memo from Stress Department: Failure of hot air valve elbow Olympus Mk.101  PA1716/5/11/2/72  12 October 1954

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Ref: 623D/7 A further vibration excitor test has been undertaken with the casing supported in a more realistic fashion and with the intention of discovering where the flexibilty lay

Bristol Aeroplane Company Olympus stress calculations. Memo from Stress Department: Olympus 6 whirling speeds  PA1716/5/11/2/73  31 October 1955

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Ref: 623D/7. Stress Department Report SV.73 dated 12 October 1955 showed the result of a test on 01.606 which suggested that the engine was whirling in the upper speed range

Bristol Aeroplane Company Olympus stress calculations. Memo from Component Development Department: Olympus exhaust annulus  PA1716/5/11/2/74  17 September 1954

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Rf: 623D/7. Frequency checks have been carried out on the turbine drain valve to OLS.809 Issue 6 fitted to the exhaust annulus ex OL.525

Bristol Aeroplane Company Olympus stress calculations. Memo from Component Development Department: Frequency checks on Olympus 101 hot air valve elbow  PA1716/5/11/2/75  13 October 1954

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Ref: 623D/7

Bristol Aeroplane Company Olympus stress calculations. Olympus 101 in Vulcan. Jet pipe modes and frequencies  PA1716/5/11/2/76  c. 1955

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Ref: 623D/7. 10 page report and calculations

Bristol Aeroplane Company. Olympus stress calculations. Olympus 301 combined heat shield and containment ring  PA1716/5/11/2/77  c. 1955

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Ref: 623D/7. 6 pages of calculations and graphs

Bristol Aeroplane Company. Olympus stress calculations. Engine de-icing system, hot air valve  PA1716/5/11/2/78  c. 1955

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Ref: 623D/7. 2 pages of calculations with drawing

Bristol Aeroplane Company. Olympus stress calculations. Drawing of Bristol Olympus turbojet  PA1716/5/11/2/79  September 1953

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Ref: 623D/7. TP.2436

Bristol Aeroplane Company. Olympus stress calculations. Olympus III modification to HP system. Increase milk churn stiffness  PA1716/5/11/2/80  c. 1953

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Ref: 6234 SR/6

Bristol Aeroplane Company. Olympus stress calculations. Olympus 6 HP system Olympus 551  PA1716/5/11/2/81  c. 1955

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Ref: 623D/6. Prog section ref: 12015/75. 9 pages of calculations and graphs

Bristol Aeroplane Company. Olympus stress calculations. Olympus 6 whirling modes. Current design  PA1716/5/11/2/82  26 October 1955

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Ref 623D/7. Graph

Bristol Aeroplane Company. Olympus stress calculations. Olympus 6 whirling modes. Current design  PA1716/5/11/2/83  26 October 1955

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Contents:
Ref: 6234SR/7

Bristol Aeroplane Company. Olympus stress calculations. Olympus 101 torsional frequency LP system  PA1716/5/11/2/84  23 June 1956

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Ref: 623D/7. 3 pages of calculations

Bristol Aeroplane Company. Olympus stress calculations. Memo from Service Department re. Olympus 101-4 auxiliary drive  PA1716/5/11/2/85  31 October 1956

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Ref: 623D/7. An investigation has been carried out recently into the possible presence and source of dangerous vibrations in the Olympus auxiliary drive system

Bristol Aeroplane Company. Olympus stress calculations. Report from Component Development Department re. Vibration tests on B.0L.101 stiffened auxiliary drive bevel gear B.126531  PA1716/5/11/2/86  12 November 1956

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Ref: 623D/7.Report 209/56. Results are shown in this report

Bristol Aeroplane Company. Olympus stress calculations. Memo from Stress Department re. Vibration tests on B.0L.101 stiffened auxiliary drive bevel gear B.126531  PA1716/5/11/2/87  21 November 1956

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Ref: 623D/7. We have now completed a calculation of the torsional critical of the system incorporating modifications detailed in the following schemes OLS.3378 Issue 5; OLS.3582 Issue 1; OLS.3381 Issue 3

Bristol Aeroplane Company. Olympus stress calculations. Olympus 101 accessory drive (driven from HP compressor) Calculations of torsional critical  PA1716/5/11/2/88  November 1956

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Ref: 623D/7. 18 pages of calculations

Bristol Aeroplane Company. Olympus stress calculations. Projected Olympus HP system whirling speed  PA1716/5/11/2/89  February 1957

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Ref: 623D/6. 12 pages of calculations and graphs

Bristol Aeroplane Company. Olympus stress calculations. Proposed spectacle plate modification to projected Olympus HP system whirling speed  PA1716/5/11/2/90  c. 1957

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Ref: 623D/6. 5 pages of calculations including graph

Bristol Aeroplane Company. Olympus stress calculations. Projected Olympus whirling speed HP system PG.670  PA1716/5/11/2/91  February 1957

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Ref: 623D/6

Bristol Aeroplane Company. Stress Department. Olympus 104 LP compressor running lines  PA1716/5/11/2/92  16 October 1959

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Performance and Power Plant Engineering Department: Graph TED23456 Olympus 104 LP compressor running lines

Bristol Aeroplane Company. Stress Department. Olympus 104 LP compressor running lines. Engine 104002 Build 12 strain gauge tests  PA1716/5/11/2/93  15 June 1959

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Performance and Power Plant Engineering Department: Graph TED22738. Titanium O and 1st stage LP rotor blades. Avro HPEGV setting

Bristol Aeroplane Company. Stress Department. Olympus 104 LP compressor running lines. Avro Flight Pipe 26.0' dia nozzle  PA1716/5/11/2/94  8 October 1959

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Issued by: Performance and Power Plant Engineering Department: Graph TED23417 Engine 104003 Build 11. Steel O stage LP rotors - 20deg LP EGV setting Engine 104008 Build 5. Aluminium O stage LP rotors - 5deg LP EGV setting Engine 104002 Build 12. Titanium O stage rotors - 20deg LP EGV setting

Bristol Aero-Engines Ltd. Stress Department. Olympus 101 Engine 10117 in Vulcan strain gauge tests  PA1716/5/11/2/95  c. 1957

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Issued by Performance & Aerodynamics Department: Graph TED9158

Bristol Aero-Engines Ltd. Stress Department. Olympus 101. Engine 10117 in Vulcan. Strain gauge tests  PA1716/5/11/2/96  c. 1957

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Issued by Performance & Aerodynamics Department: Graph TED9157. Data from curves 100% AF Factor =3.00ft/sec.

Bristol Aero-Engines Ltd. Stress Department. Minutes of meeting to discuss programme of tests on Olympus 518 in investigation of Olympus 101 1st stage LP compressor rotor blade cracking  PA1716/5/11/2/97  14 May 1957 - 29 May 1957

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Ref: CE/EW-D/HCH?9790. From Service Development - Turbine Engines and Power Plant Department. Includes related graph TT1736/1. 518/23

Bristol Aero-Engines Ltd. Stress Department. Minutes of meeting to discuss Olympus 101 1st stage LP compressor blades  PA1716/5/11/2/98  16 May 1957

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Ref: CE/EW-D/GFH/9852. From Olympus ( Production Engines Project Engineer). The object of the meeting was to review the action being taken as a result of the failure of the 1st stage LP compressor blades of the 3 lobed root type in Engine 101045 installed in Vulcan XA898 in No.2 position, and the cracking of the 2 lobed root 1st stage blades (R-R.58) in flight engines at hours varying between 150 and 200. Examination of the flight programme of Vulcan XA.898 operating in the RAF showed that there had been a considerable amount of low flying whereas strain gauging in the air on the 2 lobed root had in the main been done at altitudes above 20,000 ft. As a result of this Vulcan XA.891 flew strain guage tests with Engine No.10117 (installed in in No.2 position) fitted with 3 lobed root blades at altitudes up to 10,000 ft at varying aircraft speeds, and throughout the speed range of the engine. Includes 3 related graphs

Bristol Aero-Engines Ltd. Stress Department. Minutes of meeting to discuss Olympus 101 1st stage LP compressor blades  PA1716/5/11/2/99  5 July 1957

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Ref: CE/EW-D/GFH/10589. From Olympus (Production Engines - Project Engineer). The object of the meeting was to review further work being done on strain gauging, aerodynamic tests and mechanical tests to improve the overhaul life of the 1st stage LP compressor blades in the Olympus 101 engines, and to establish the flight life of 102 and 104 engines relative to zero and 1st stage LP compressor blades

Bristol Aero-Engines Ltd. Stress Department. Discussion of strain gauge results of 10132 to explain failure of Engine 10131 and 519 and recommend future action  PA1716/5/11/2/100  11 July 1957

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Blade Engineering Department: Notes on a meeting in Mr Blackwell's office 11 July 1957. 1.0. Strain gauge testing. 2.0 Analysis of strain gauge results. 2.1 Standard engine (Test 1a). 2.2 Venturi engine (Test 2). 2.3 Canberra intake and venturi nozzles (Test 3). 2.4 Test at -20deg EGV setting. 3.0 Discussion of results. 3.1 Effect of intake. 3.2 Effect of nozzle. 3.3 Effect of trimmers. 3.4 Explanation of failure of 519. 4.0 Future testing. 5.0 Flutter margin of Olympus 102 engines

Bristol Aero-Engines Ltd. Stress Department. Summary of tests on the aerodynamic condition in the Vulcan intake ducts  PA1716/5/11/2/101  17 September 1957

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Project Department: Ref GN2066: From Project Department. Following the 1st stage compressor blade failure of an Olympus 101 in Vulcan XA898 at Waddington, it was realised that little was known about the aerodynamic flow conditions at the Olympus engine face of this aircraft. Since the aerodynamic reason for the blade failure was unknown, a series of tests were carried out by BAE and Avros to obtain more information about conditions prevailing in the intake duct. The test carried out by BAE were on a full scale Olympus 102 engine in the Vulcan wing rig and only simulated ground running. Whereas the Avro tests were on a 1/7.5 scale model of a wing fuelage combination carried out in a number of flight attitudes as well as the ground running case

Bristol Aero-Engines Ltd. Stress Department. B.OL 102046(3) 2nd bench test. SG O & 1st stage LP compressor rotor blades  PA1716/5/11/2/102  17 January 1958

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Bristol Aero-Engines Ltd. Stress Department. Graph 6. 1st stage blade No.183. B.OL 102046(3) 2nd bench test SG O & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/1  16 January 1958

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JRH. Graph 1: O stage blade 183. 100 rpm increments. 26' dia nozzle without trimmers

Bristol Aero-Engines Ltd. Stress Department. Graph 5. 'O' stage blade No.179. B.OL 102046(3) 2nd bench test. SG 'O' & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/2  16 January 1958

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JRH Graph 5: 1st stage blade 183. 100 rpm increments. 24.5' dia nozzle without trimmers

Bristol Aero-Engines Ltd. Stress Department. 'O' stage blade No.179. B.OL 102046(3) 2nd bench test. SG O & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/3  17 January 1958

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Contents:
JRH Graph: 1st stage blade 179. 100 rpm increments. Acceleration 26' dia nozzle

Bristol Aero-Engines Ltd. Stress Department. Graph 'O' stage blade No.179. B.OL 102046(3) 2nd bench test. SG 'O' & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/4  17 January 1958

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Graph 7: 1st stage blade 179. 100 rpm increments. 26' dia nozzle without trimmers. LP compressor rpm

Bristol Aero-Engines Ltd. Stress Department. Graph 'O' stage blade No.179. B.OL 102046(3) 2nd bench test. SG 'O' & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/5  16 January 1958

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Graph 9: 'O' stage blade 179. 100 rpm increments. 22.4' dia nozzle without trimmers. LP compressor rpm

Bristol Aero-Engines Ltd. Stress Department. Graph 1st stage blade No.183. B.OL 102046(3) 2nd bench test SG O & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/6  17 January 1958

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Graph 6: 1st stage blade No.179. 100 rpm increments. 22.4' dia nozzle with trimmers

Bristol Aero-Engines Ltd. Stress Department. Graph 1st stage blade No.183. B.OL 102046(3) 2nd bench test SG O & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/7  16 January 1958

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Contents:
Graph 2: 1st stage blade 183. 100 rpm increments. 26' dia nozzle without trimmers. LP compressor rpm. JET. ESE

Bristol Aero-Engines Ltd. Stress Department. Graph 1st stage blade No.183. B.OL 102046(3) 2nd bench test SG O & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/8  17 January 1958

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Contents:
Graph 10: 1st stage blade 183. 100 rpm increments. Acceleration. 26' dia nozzle. LP compressor rpm

Bristol Aero-Engines Ltd. Stress Department. Graph 1st stage blade No.179. B.OL 102046(3) 2nd bench test. SG 'O' & 1st stage LP compressor rotor blades  PA1716/5/11/2/102/9  16 January 1958

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Contents:
Graph: 1st stage blade 179. 100 rpm increments. 24' dia nozzle with trimmers. LP compressor rpm. ESE. JET

Bristol Aero-Engines Ltd. Stress Department. Graph 4 B.OL 102046(3) 2nd bench test SGO & 1st stage LP compressor rotor blades. LP compressor rpm.  PA1716/5/11/2/102/10  16 January 1958

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Contents:
JRH. Graph 4: 1st stage blade 183. 100 rpm increments. 22.4' dia nozzle without trimmers

Bristol Aero-Engines Ltd. Stress Department. Olympus 104 failure of zero stage compressor blades in Canberra  PA1716/5/11/2/103  20 January 1958

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Ref: CE/PFG/123. From PF Green to Sir W Alec Corton. The recent failure of the port engine 104006 in the Canberra after 17 hours flying time has been established as originating from fatigue failure of two zero stage LP compressor blades just above the blade root platform, the crack starting from the leading edge. The marking on the blade root serrations on this stage was not abnormal, but the first stage blade root serrations were heavily fretted

Bristol Aero-Engines Ltd. Stress Department. Olympus zero stage LP compressor rotor blade failure in Canberra WH713 on 14 January 1958. Minutes of meeting held on 15 January 1958  PA1716/5/11/2/104  21 January 1958

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Ref: CE/EW-D/HCH/13350. From Service Department - Turbine Engines and Power Plant. The meeting was held to discuss the cause and effects of the zero stage blades on Olympus 104 engine No.104006 in the port position of the Canberra aircraft whilst on take-off

Bristol Aero-Engines Ltd. Stress Department. Olympus 102 & 104 motorised throttle, strain gauging & endurance testing of zero & 1st stage blades  PA1716/5/11/2/105  24 January 1958

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Ref: CE/EW-D/GFH/13436: From Olympus (Production Engines) Project Engineer. The development programme agreed to investigate the resonant conditions of the zero and first stage blades in R-R58 and the programme to clear the same blades in steel for the Olympus 104 is a follows: 1 Engine No.101046. 2 Engine No.104003. 3 Engine No.104002. 4 Engine No.102007. 5. Page 2 of this report is missing

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 102046 (4th Build). Flight standard Olympus 102  PA1716/5/11/2/106  30 January 1958

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Ref: CE/LBJ/EKA/7214. Mechanical Research department. The test is primarily to establish whether the amplitude of vibration in the 1F and 2F modes of the zero and first stage blades are significantly different from those of the Olympus 104 engines. It is also intended to explore the speed range between 800 rpm and 2,100 rpm to establish whether there is a severe vibration which would explain the 104 Canberra failure

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 104003. Establishment of conditions for motorised throttle test  PA1716/5/11/2/107  30 January 1958

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Ref: CE/LBJ/EKA/7217. Mechanical Research Department. In order to carry out an endurance test on the zero and first stage blades of an Olympus 104 engine which will be comparable to the most serious flight conditions, it is necessary to increase the amplitude of vibration which are normally obtained on the test bed.

Bristol Aero-Engines Ltd. Stress Department. Olympus 102 & 104 the effect of high forward speed on LP compressor running lines  PA1716/5/11/2/108  6 February 1958

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Performance Department No.225. Strain gauging tests carried out on the Olympus 102 & 104 in the Vulcan have shown that high forward speeds increase the amplitudes of vibration of the zero and first stage LP compressor. This has prompted an investigation into the effect of high forward speed on the LP compressor operating lines. A comparison has also been made of the test bed running lines for several standards of Olympus 102 and 04 engines. High forward speed at low altitude move the LP compressor nearer surge when the engine is running at low engine speeds. This only applies to the engine speed range where the engine final nozzle is unchoked on the test bed. The non-dimensional conditions obtained at high forward speed can be simulated to some extent by running the engine on the test bed with larger final nozzles. Pressure levels will, of course, be lower on the test bed

Bristol Aero-Engines Ltd. Stress Department. Olympus 104 in Canberra WH713. Notes on the preliminary meeting to lay a framework for the Flight test schedules covering the vibration measurements now being planned on zero and 1st stage rotor blades of the LP compressor  PA1716/5/11/2/109  6 February 1958

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Ref: CE/LBJ/ACN/7228. Mechanical Research Department. Engine operational history before failure (Ref: CE/AJT/ESG/3217. The tables showing a 'break-down' of the port engine (B.0L.104006) running time to failure were examined again. Full details of the last six performance flights were given by Mr Zanker and are summerised in this report

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 102015. Establishment of conditions for motorised throttle test  PA1716/5/11/2/110  20 February 1958

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Ref CE/LEJ/EKA. Mechanical Research Department. MRD Tech -Memo No.153/58

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 104002. Bench test prior to flight test in Canberra WH713  PA1716/5/11/2/111  4 March 1958

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Ref: CE/LBJ/ACN/7228. Mechanical Research Department. Technical Memorandum 157/58. The tests are to establish the amplitudes of vibration of the blading obtainable on the test bed for comparison with the flight results. The results will also enable the two blades to be used during the flight tests to be selected

Bristol Aero-Engines Ltd. Stress Department. Olympus 104 in Canberra WH713. Notes on the meeting to finalise the programme of flight testing on the 1st strain gauge engine No.104002 in the Canberra  PA1716/5/11/2/112  7 March 1958

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Ref: CE/LBJ/RNTR/7279. Mechanical Research Department. Engine No.104002 with the R-R58 'O' stage rotor blades will be available on the 12 March

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 102007(9). Survey and endurance tests on steel zero & 1st stage rotors  PA1716/5/11/2/113  12 March 1958

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Ref: CE/LBJ/EKA/7296. Mechanical Research Department. No.2 Shadow

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 104003(8). Bench test prior to flight test in Canberra  PA1716/5/11/2/114  14 April 1958

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Ref: CE/LBJ/EKA/7361. Mechanical Research Department

Bristol Aero-Engines Ltd. Stress Department. Flight strain gauge programme for Olympus 104003(8) in Canberra  PA1716/5/11/2/115  1 May 1958

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Ref: CE/LBJ/EKA/7398. Mechanical Research Department. The aim of the test series is to establish that the steel blades in the zero and 1st stages will operate satisfactorily during flight testing in the Canberra. On a previous flight with an R-R58 bladed engine, large amplitudes of vibration in the fundamental flexural mode were observed at 45,000 and 50,000 ft. The test programme will broadly follow that used during the investigational flight into the recent Canberra failure, but will be extended to include as many operational conditions as possible

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 104008(5). Aluminium'O' and 1st stage bench test and Vulcan flight tests  PA1716/5/11/2/116  21 May 1958

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Ref: CE/LBJ/EKA/7439. Mechanical Research Department. The aim of the flight test is to determine whether the large amplitudes of vibration, which were found on the zero and 1st stage rotor blades in the Canberra engine at 50,000 ft exist; also an aluminium zero stage and 1st stage when in a Vulcan. The maximum altitude covered in detail by the previous flight tests was 40,000 feet

Bristol Aero-Engines Ltd. Stress Department. Modification to the strain gauge programme for Olympus 104003(8) in Canberra  PA1716/5/11/2/117  13 June 1958

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Ref: CE/LBJ/EKA/7475. Mechanical Research Department. During the second flight (No.40 & No.41) of the series to the modified programme CE/LBJ/EKA/7470 at 45,000 ft, the engine speed, while the aircraft was accelerating, was not held constant. It is thus proposed to repeat this part of the test during the third flight of the series (flight No.42). This may be achieved by coupling 2 'O' stage and 2 1st stage blades into the recorder. The detail requirements for the third flight as listed in this report

Bristol Aero-Engines Ltd. Stress Department. Revised strain gauge programme for Olympus 104008(5). Aluminium 'O' and 1st stage ground and Vulcan flight tests  PA1716/5/11/2/118  19 June 1958

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Ref: CE/LBJ/EKA/7493. Mechanical Research Department

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for bench tests on Olympus 102015(13)  PA1716/5/11/2/119  27 June 1958

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Ref: CE/LBJ/RNTB/7512. Mechanical Research Department. A meeting was held on Wednesday 25 June to formulate a strain gauge programme and determine the motorised throttle running to be carried out on the steel zero and 1st stage rotor blades

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for bench tests on Olympus 102015(13). Addition to the programme CE/LBJ/RNTB/7512 27 June 1958  PA1716/5/11/2/120  1 July 1958

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Ref: CE/LBJ/EKA/7519. Mechanical Research Department

Bristol Aero-Engines Ltd. Stress Department. A discussion on the effect of working life on vibration amplitudes of the Olympus 104 engine in the Canberra and Vulcan  PA1716/5/11/2/121  22 July 1958

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Mechanical Research Department. Tech- memo 205/58. A meeting was held in the Stress Office Conference Room on 18 July 1958. The meeting was held in the Stress Office on 18 July, in order to find some plausible explanation of why the 104 engine behaves differently in the Canberra and Vulcan. Past strain tests have shown that at altitudes of up to 20,000 ft large ampitudes of vibration are present over the zero stage blades of the Vulcan, which are not present over the same range in the Canberra. Tests on both aluminium and steel blades on the Canberra have shown large amplitudes at high altitudes which are absent on the Vulcan

Bristol Aero-Engines Ltd. Stress Department. Strain gauge tests on 1st, 2nd & 3rd LP stators of Olympus 6 engine 607  PA1716/5/11/2/122  29 July 1958

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Ref: CE/LBJ/EKA/7570. Mechanical Research Department. In order to improve the impact resonance of the LP blading assembly of the Olympus 6 engines, a scheme has been drawn up in which the stator platforms are bolted to the casing. A strain gauge test is to be carried out to compare the amplitudes of vibration of the blades with hose for the previous standard loose dovetail fixing

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus 104008(5). Effect of nozzle & EGV settings  PA1716/5/11/2/123  28 July 1958

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Memo: CE/LBJ/EKA/7566. Mechanical Research Department. During development running with the cooled turbine on engine No.101016, an LP compressor failure occurred. This was found to be due to a 1st stage blade failure. Due to the effects of the cooled turbine, the LP running line of the engine was moved much nearer surge than a standard engine. One aspect of the present testing is to reproduce this running line and see if there is significant increase in blade vibration amplitudes on the zero and 1st stage

Bristol Aero-Engines Ltd. Stress Department. Flight strain gauge programme Olympus 104003(9). Steel 'O' & 1st stage rotors - ground & Vulcan tests  PA1716/5/11/2/124  30 July 1958

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Memo: CE/LBJ/EKA/7572. Mechanical Research Department. The basic purpose of the test series is to confirm the dangerous amplitudes of vibration obtained during flight strain gauge testing of Olympus 104004(3) have been reduced to a satisfactory level by use of steel blading in the zero and 1st stages. The programme is then intended to be extended to clear the blading over much of the operational range as practical

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme Olympus engine 528(20). Titanium 1st stage LP compressor rotor blades  PA1716/5/11/2/125  18 July 1958

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Ref: CE/LBJ/EKA/7548. Mechanical Research Department. The aim of the tests is to examine the characteristics of vibration of Titanium blading. This stage has been chosen since comparative test results are available in both aluminium and steel

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for the final flight of Olympus 104003(9) in the Vulcan. Steel 'O' and 1st stage rotors  PA1716/5/11/2/126  29 August 1958

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Memo: CE/LBJ/EKA/7623. Mechanical Research Department. The aim of this series of tests is to observe if any dangerous amplitudes are caused by the attitude of the aircraft or by any other aircraft or engine manoeuvres of a special nature which are part of normal service procedure

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for bench testing Olympus 102015(13) at Brockworth and Bristol  PA1716/5/11/2/127  21 August 1958

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Mechanical Research Department. No.2 shadow

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus engine 528(21). Establishment of conditions for motorised throttle test. Titanium 1st stage LP compressor rotor blades  PA1716/5/11/2/128  4 November 1958

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Tech Memo: 225/58 Mechanical Research Department

Bristol Aero-Engines Ltd. Stress Department. Strain gauge programme for Olympus engine 104003(11). Steel 'O' and 1st stage LP rotors. Effect of large nozzles & EGV settings  PA1716/5/11/2/129  5 November 1958

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Ref: CE/LBJ/EKA/77433. Mechanical Research Department

Bristol Aero-Engines Ltd. Stress Department. Vulcan XA889.LP compressor running lines. Engine Olympus 104 Build 9. 22.4' diameter jet pipe nozzle  PA1716/5/11/2/130  30 September 1958

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Ref: CE/LBJ/EKA/1563. Installation and Flight Development Department

Armstrong Siddeley Motors Ltd, Brockworth: Performance results obtained during strain gauge testing of Olympus 104 engine 102015 on No.3 Gipsy Patch and No.10 Brockworth test beds  PA1716/5/11/2/131  13 October 1958

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Ref: STR/J/E/50

Bristol Aeroplane Co Ltd. Stress Department: Strain gauge programme for Olympus engine 102046(Build 7). Aluminium 'O' and 1st stage LP rotors  PA1716/5/11/2/132  25 March 1959

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Ref: CE/LBJ/DAB/8054. Mechanical Research Department

Bristol Siddeley Engines Ltd. Stress Department: Strain gauge programme for Olympus engine 104001. 'O' and 1st & 2nd stage LP rotors & No.3 bearing diaphragm. Pre-flight bench test  PA1716/5/11/2/133  4 May 1959

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Bristol Aeroplane Co. Ltd. Stress Department: Table summary of Olympus 102 & 104  PA1716/5/11/2/134  c. 1958

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Bristol Aeroplane Co. Ltd. Stress Department: Table summary of Olympus 102 & 104 blade amplitudes in flight  PA1716/5/11/2/134/1  c. 1958

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Contents:
Both turbines similar ie, +10% HP/+5% LP and steel N

Bristol Aeroplane Co Ltd. Stress Department: Table summary of effects of EGV setting on Olympus 104 blade amplitudes (Test bed)  PA1716/5/11/2/134/2  c. 1958

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Contents:
Maximum amplitudes and rpm given

Letter from Avro to Bristol Aeroplane Co Ltd. Stress Department: Preliminary data on the swirl on the 1/7.5 scale Vulcan model  PA1716/5/11/2/135  18 June 1957

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Olympus Jet pipe characteristics. From LE Leavy, Superintendent Wind Tunnels, Aircraft Research Division: I enclose some preliminary data on the swirl which we measured under flight conditions on the 1/.7.5 scale Vulcan model. This information should be treated as preliminary as we have as yet no accurate knowledge of the velocity in the engine duct, consequently the values Vo/VE quoted on the diagrams have a probable accuracy of no more than +10%. 4 graphs attached showing swirl in the engine ducts of the 1/7.5 scale Vulcan

Bristol Aeroplane Co Ltd. Stress Department: Graphs for Olympus 102 & 104  PA1716/5/11/2/136  1954 - 1957

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Bristol Aeroplane Co Ltd. Stress Department: Graph Olympus 102 Ashton OARW4 Jet pipe Olympus 102 NO.517 Build 11  PA1716/5/11/2/136/1  2 August 1955

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22.5' Nominal inclined flight nozzle (shrouded)

Bristol Aeroplane Co Ltd. Stress Department: Graph Olympus 102 Ashton OARW4 Jet pipe Olympus 102 NO.517 Build 11  PA1716/5/11/2/136/2  2 August 1955

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Contents:
22.5' Nominal inclined flight nozzle (shrouded) + 6 trimmers

Bristol Aeroplane Co Ltd. Stress Department: Graph Olympus 104 Production Jet pipe  PA1716/5/11/2/136/3  c. 1955

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Contents:
22.436' Production jet pipe l

Bristol Aeroplane Co Ltd. Stress Department: Graph TED.5241/B Jet pipe characteristics for Olympus 102 & 104  PA1716/5/11/2/136/4  18 July 1957

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Issued by the Performance & Aerodynamics Department Engine Division Filton Bristol. Drawn by DWL

Bristol Aeroplane Co Ltd. Stress Department: Graph TED.4741/D Jet pipe characteristics for Olympus 102 & 104  PA1716/5/11/2/136/5  15 November 1954

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Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/137  1 January 1953

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 22.6'. Exit nozzle diameter 20.5'. Graph TED.2561. (Superceding TED.2122 & 2122A)

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics. Based on calibrations of Olympus 510 Build 4 & 511 Build 5  PA1716/5/11/2/138  26 February 1953

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 22.6'. Exit nozzle diameter 20.5'. Graph TED.2697

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/139  27 April 1953

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 24.5'. Exit nozzle diameter 21'. Graph TED.2756. Test bed obtained from Olympus 510 Build 5. Olympus 511 Build 6. Olympus 511 Build 7

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/140  18 March 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by JYB. Jet pipe diameter 24.5'. Exit nozzle diameter 21.5'. Graph TED.3943. Superseded by TED.4390. Test points for 1/2B Olympus engine 511 Build 12 shown on curves

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/141  18 March 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by JYB Jet pipe diameter 24.5'. Exit nozzle diameter 22'. Graph TED.3944. Test points for 1/2B Olympus engine 511 Build 12 shown on curves

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/142  21 May 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 24.5'. Jet nozzle diameter 21.25'. Graph TED.4142. Note: In the absence of test results. These characteristics assume thrust and discharge coefficients taken from TED.2756 (characteristics with 21' nozzle). A new curve will be issued when test results are available

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/143  9 July 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 24.5'. Jet nozzle diameter 21.25'. Actual nozzle diameter 21.203. Graph TED.4304. Test results: Olympus 101 No.523 Buiild 4 & 5

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/144  18 August 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 24.5'. Jet nozzle diameter 21.25'. Based on test results obtained with Olympus 101 Engine No.523/5. Graph TED.4390

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/145  19 August 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC Jet pipe diameter 24.5'. Jet nozzle diameter 20.5'. Based on test results obtained with Olympus 101 Engine No.523/5. Graph TED.4391

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/146  20 August 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 24.5'. Jet nozzle diameter 21'. Curve based on test results for Olympus 101 Engine No.523/5. Graph TED.4401

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/147  3 September 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 24.5'. Jet nozzle diameter 21.203 (Actual)'. Test result Olympus 101 Engine 521 Build 9. A= Test results (21.177' nozzle) Olympus 521/10. TED.4491

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/148  30 November 1954

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 24.5'. Jet nozzle diameter 21.203 (Actual)'. Test result Olympus 101 Engine 521 Build 9. Also Engine 522 Build 9. A= Test results (21.177' nozzle) Olympus 521/10. TED.4491

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/149  20 January 1955

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 24.5'. Jet nozzle diameter 21.4' (Actual 21.396'). Test result Olympus 101 Engine 521 Build 10. TED.4992B

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/150  12 April 1955

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Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 24.5'. Jet nozzle diameter 21.4' with 1 trimmer. Curve based on test for Olympus 101 Engine 523 Build 7. TED.5485

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics  PA1716/5/11/2/151  26 July 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Jet pipe diameter 24.5'. Jet nozzle diameter 22.6'(nominal). 522 22.591'(actual); 521 22.562'(actual). Curve based on test results for Olympus 98Z Engine No.522 Build 11 TED.6015 (superceded by TED6945)

Bristol Aeroplane Co Ltd. Stress Department: Canberra Jet pipe characteristics.  PA1716/5/11/2/152  13 October 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 24.5';Jet nozzle diameter 23' (nominal). 23.060(actual). Curve based on test for Olympus Engine 521 Build 14. Olympus Engine 522 Build 15. TED.6522

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102  PA1716/5/11/2/153  12 January 1956

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Jet pipe diameter 22.5'; Jet nozzle diameter 22.6'. (Superceding TED.6015). Drawn by DWL

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102 Avro jet pipe characteristics Airflow function vs thrust  PA1716/5/11/2/154  16 January 1956

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. 27' diameter Avro pipe; 22.389' diameter inclined flight nozzle. TED.6987. This curve is consistent with TED.6091 Issue 2. Engine No.10132 Build 2 No,2.GP. 26.7555. TED.6987

Bristol Aeroplane Co Ltd. Stress Department: Olympus 104 jet pipe characteristics  PA1716/5/11/2/155  14 November 1957

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 24.5' diameter Canberra jet pipe; 22.6' nominal diameter nozzle. Gross jet thrust. TED.20049

Bristol Aeroplane Co Ltd. Stress Department: Olympus 104 jet pipe characteristics  PA1716/5/11/2/156  14 November 1957

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 24.5' diameter Canberra jet pipe (old type RCJ 4 CS 4120); 22.6' nominal diameter nozzle (old type 4 statio tappings). Mass flow. New curves drawn for Nimonic or st.steel. Jet pipe with 8 tappings. TED.20048

Bristol Aeroplane Co Ltd. Stress Department: Olympus 104 jet pipe characteristics  PA1716/5/11/2/157  18 April 1958

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 24.5' diameter Nimonic or stainless steel jet pipe to latest standard (B.Static tappings) 22.6' nominal diameter nozzle. TED.20790

Bristol Aeroplane Co Ltd. Stress Department: Olympus 104 jet pipe characteristics  PA1716/5/11/2/158  18 April 1958

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 24.5' diameter Nimonic or stainless steel jet pipe to latest standard (B.Static tappings) 22.6' nominal diameter nozzle. Gross jet thrust. TED.20789

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102 Avro jet pipe characteristics. Mass flow  PA1716/5/11/2/159  8 November 1956

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. 27' diameter Avro jet pipe. 22.4' diameter flight nozzle. TED.8208

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102 Avro jet pipe characteristics. Gross thrust  PA1716/5/11/2/160  8 November 1956

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. 27' Avro diameter jet pipe. 22.4' diameter flight nozzle. TED.8207

Bristol Aeroplane Co Ltd. Stress Department: Olympus 100 jet pipe characteristics  PA1716/5/11/2/161  15 May 1953

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 27'; Jet nozzle diameter 21.75'.TED.2895

Bristol Aeroplane Co Ltd. Stress Department: Olympus 100 Avro jet pipe characteristics  PA1716/5/11/2/162  15 May 1953

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 27'; Jet nozzle diameter 21.75'.TED.2895

Bristol Aeroplane Co Ltd. Stress Department: Olympus Avro jet pipe characteristics  PA1716/5/11/2/163  15 May 1953

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 27'; Jet nozzle diameter 21.75'.TED.3445. Calibrated on Engine No.2603 Build 14

Bristol Aeroplane Co Ltd. Stress Department: Olympus. Avro jet pipe characteristics  PA1716/5/11/2/164  1 February 1954

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 27'; Jet nozzle diameter 20.75'(nominal) with trimmers.TED.3813

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101. Avro jet pipe characteristic  PA1716/5/11/2/165  21 October 1954

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Jet pipe diameter 27'; Jet nozzle diameter 21.2'(nominal) with trimmers.TED.4654B

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101. Characteristics of Avro jet pipe with 21.3' dia nozzle  PA1716/5/11/2/166  8 December 1954

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Covering ground run range only. TED4827

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101. Characteristics of 27' Avro jet pipe with 21.3' dia nozzle  PA1716/5/11/2/167  21 January 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Supercedes TED.4827)

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101 jet pipe Characteristics  PA1716/5/11/2/168  9 March 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. Production jet pipe: 21.3'nozzle with one 3/16'th by 10'. TED.5275

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101 jet pipe Characteristics  PA1716/5/11/2/169  7 April 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DC. Production jet pipe: Final nozzle diameter 21.3'; Cone angle 24deg (included). TED.5464

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102 jet pipe Characteristics. Production jet pipe  PA1716/5/11/2/170  1 August 1956

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Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. 22.55' diameter nozzle with trimmers. Note: In the absence of results, this curve has been taken to be the same as that for the Acr pipe with 22.413' diameter flight nozzle plotted on TED.6091. TED.7817

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102 jet pipe Characteristics. Production pipe  PA1716/5/11/2/171  1 August 1956

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. 22.55' diameter nozzle with trimmers. TED.7816

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101Z jet pipe Characteristics. 27' dia production slave jet pipe  PA1716/5/11/2/172  9 August 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. 22.423' diameter nozzle with two trimmers (7.5' by 1/4'). TED6090

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101. Jet pipe Characteristics for Vulcan jet pipe  PA1716/5/11/2/173  8 December 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. TED.6824

Bristol Aeroplane Co Ltd. Stress Department: Olympus 101Z. Avro jet pipe Characteristics  PA1716/5/11/2/174  9 August 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. 27' diameter Avro jet pipe. 22.389' diameter inclined fight nozzle. TED.6091. Issue 2

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102 Avro jet pipe Characteristics  PA1716/5/11/2/175  11 April 1956

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. 27' diameter pipe. 22.389' dia nozzle. NB: Both jet pipe and static pressure were measured at front of pipe. TED.7330

Bristol Aeroplane Co Ltd. Stress Department: Olympus. Characteristics for Avro jet pipe with 21.3' dia nozzle 20.2' long  PA1716/5/11/2/176  17 April 1956

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. Note: In the absence of test data these characteristics have been based on the thrust and discharge coefficients used in preparing the 21.2' nozzle curves given on TED.5241. TED.7342

Bristol Aeroplane Co Ltd. Stress Department:Olympus. Characteristics for Avro jet pipe with 21.2' dia nozzle 20.2' long  PA1716/5/11/2/177  20 April 1956 - 23 April 1956

2 Items

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. NB: This curve is consistent with TED.5241. Includes related graph - 27' dia Avro jet pipe; 22.4' dia (nominal) flight nozzle. TED.7352 (Supercedes TED.7330)

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102. Engine No.527 Build 7. Jet pipe Characteristic. Avro jet pipe (ORW40) and 22.4' dia machined slave nozzle  PA1716/5/11/2/178  17 May 1956

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Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. TED.7482

Bristol Aeroplane Co Ltd. Stress Department:Olympus 102. Engine No.527 Build 7. Jet pipe Characteristic. Avro jet pipe (ORW40) and 23.6' dia nozzle  PA1716/5/11/2/179  17 May 1956 - 28 January 1957

2 Items

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. TED.7483 and 27' dia jet pipe; 22.4' dia nozzle with 24 square' trimmer area. TED.20382

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102. Avro jet pipe characteristic airflow vs thrust 27' dia Avro pipe with 22.4' dia flight nozzle  PA1716/5/11/2/180  18 March 1957

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Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by DWL. This curve is consistent with TED.8207 & 8. TED.8955

Bristol Aeroplane Co Ltd. Stress Department: Olympus. Avro jet pipe characteristics  PA1716/5/11/2/181  26 April 1957

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by FGY. 27'dia Avro jet pipe; 22.4' dia (nominal) flight nozzle with 4 bar trimmers. TED.9100

Bristol Aeroplane Co Ltd. Stress Department: Olympus. Avro jet pipe characteristics (Mass flow)  PA1716/5/11/2/182  27 June 1957

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by FGY. 27' dia Avro jet pipe; 22.4' dia nozzle with 6 aerodynamic trimmers (each 4'square). Data from Engine No.526 Build 24. TED.9406

Bristol Aeroplane Co Ltd. Stress Department: Olympus. Avro jet pipe characteristics (Thrust)  PA1716/5/11/2/183  27 June 1957

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by FGY. 27' dia jet pipe; 22.4' dia nozzle with 6 aerodynamic trimmers (each 4 square'). Data from Engine No.526. Build 24. TED.9407

Bristol Aeroplane Co Ltd. Stress Department: Olympus 104. Avro jet pipe characteristics (Gross thrust)  PA1716/5/11/2/184  4 November 1957

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 27' dia Avro jet pipe; 22.4' dia nozzle with 6 square' trimmers aera. TED.9976

Bristol Aeroplane Co Ltd. Stress Department: Olympus 104. Avro jet pipe characteristics (Mass flow)  PA1716/5/11/2/185  4 November 1957

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 27' dia Avro jet pipe; 22.4' dia nozzle with 6 square' trimmers aera. TED.9977

Bristol Aeroplane Co Ltd. Stress Department: Olympus 104. Avro jet pipe characteristics (Mass flow)  PA1716/5/11/2/186  28 January 1958

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 27' dia Avro jet pipe; 22.4' dia nozzle with 6 square' trimmers aera. TED.20381 (Supercedes TED.9406)

Bristol Aeroplane Co Ltd. Stress Department: Olympus 102. Ashton jet pipe characteristics  PA1716/5/11/2/187  21 February 1955

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. 27' dia jet pipe; 21.75' dia slave nozzle. TED.5152

Bristol Aeroplane Co Ltd. Stress Department:Olympus 102. Ashton jet pipe characteristics. Air mass flow  PA1716/5/11/2/188  11 November 1958

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. Based on ground run of port engine No.527 Build 10 on 5 November 1958 with venture intake. 22.5 nom dia nozzle with 30 square' trimmer area. Air mass flow. TED.21638

Bristol Aeroplane Co Ltd. Stress Department:Olympus 102. Ashton jet pipe characteristics. Air mass flow  PA1716/5/11/2/189  11 November 1958

1 Item

Contents:
Issued by the Performance & Aerodynamic Department. Engine Division Filton Bristol. Drawn by EAW. Based on ground run of starboard engine No.522 Build 31 on 6 November 1958 with venture intake. 22.5 nom dia nozzle with 15 square' trimmer area. Air mass flow. TED.21637

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus low pressure compressor. To determine the axial thrust and the torque in the compressor rotor  PA1716/5/11/2/190  c. 1951

Contents:
Ref: 434c.1/3. 4-page report and calculations

Experimental Inspection Department Report No: T.237/59, Olympus Mk.104, Burner Leakage Investigation, removal and bulk strip of turbine on completion of test  PA1716/5/11/2/191  23 June 1959

1 Item

Laboratory Initiation No.8607, Report No.99: No.5 Roller Bearing F.B.193743 Ex Ol.1011038 Mk.102  PA1716/5/11/2/192  20 March 1957

1 Item

Bristol Aero-Engines Ltd: Defects Investigation Department, Report AM/D. 3866, Vulcan Mk.1  PA1716/5/11/2/193  11 December 1958

1 Item

Laboratory Initiation No.8607, Report No.168: No.5 Roller Bearing B.207593 FX OL.101032  PA1716/5/11/2/194  26 January 1959

1 Item

Report on Investigation No.106(T), Olympus 6  PA1716/5/11/2/195  7 January 1957

1 Item

Experimental Department Report No.365/59: Olympus Mk.104, Tria of roller bearing cage test blocks with roller retaining lugs  PA1716/5/11/2/196  9 March 1959

1 Item

Laboratory Initiation No.8607, Report No.178: No.5 Bearing FB.193743 EX Olympus 104, Engine No.104559  PA1716/5/11/2/197  30 April 1959

1 Item

Bristol Siddeley Engines Ltd Defects Investigation Department: Vulcan B.Mk.1 XH.497  PA1716/5/11/2/198  10 June 1959

1 Item

Olympus 101 Engine Test Report, Build No. 22 & 23, Engine No. 528  PA1716/5/11/2/199  1 December 1959

1 Item

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus low pressure compressor rotor blades  PA1716/5/11/2/200  c. 1951

Contents:
Ref: 434c.1/4. Estimation of weight of blade above base (2nd group). 8-page report and calculations. Drawing of 4th stage; Root sections

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. Olympus LP compressor driving shaft  PA1716/5/11/2/202  11 July 1951

Contents:
Ref:434c.1/3. Design memo GDM/BE.10/71. Olympus front section compressor driving shaft B.51025; calculations attached KWF/VAK

Bristol Aero-Engines Ltd. Stress Department. Static test on starter drive shear neck  PA1716/5/11/2/203  9 April 1952 - 28 March 1955

1 Item

Contents:
5214SR/17. Drawing of parts tested: B.47197. The starter drive shear neck has been subjected to a static load/deflection test in order to determine the yield and ultimate torques for comparison with for comparison with the design failing torque of 110lb.ft. An applied torque of 108lb.ft caused marked yielding, and the neck shared at 125lb.ft.

Bristol Gas Turbines: Olympus Mk.1/2 stress investigation. LP compressor rotor tail shaft. The stresses in the tail shaft due to misalignment at the compressor turbine coupling  PA1716/5/11/2/204  c. 1951

1 Item

Contents:
Ref: 434c.SR/3. report and calculations

Letter from Ransome & Marles Bearing Co. Ltd. to Bristol Aeroplane Co. Ltd Stress Department. Bearings for overspeed generator drive in Olympus 1/2B  PA1716/5/11/2/205  7 August 1952 - 13 August 1959

1 Item

Contents:
5214SR/18 As promised by Mr Stockdon during today's telephone conversation we give the part numbers for the above bearings: MRJ.15 - FB.196110 (inner, bage and rollers). XRJ.11/2 - FB .196111 (cage and rollers). XIJ.11/2 - FBS.225/12/AZB.

Bristol Gas Turbines Stress Department: Letter to Ransome & Marles Bearing Co. Ltd. Bearings for overspeed generator drive in Olympus 1/2B  PA1716/5/11/2/206  18 June 1952

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Contents:
5214SR/18. We are enclosing herewith a copy of our scheme MS.1453 which gives preliminary details of the bearings and their running conditions in the above drive

Bristol Gas Turbines: Stress Department Letter from Ransome & Marles Bearing Co. Ltd. Bearings for overspeed generator drive in Olympus 1/2B  PA1716/5/11/2/207  1 July 1952

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Contents:
5214SR/18. We are enclosing prints illustrating the inner, cage and rollers of our LRJ.17 and the cage and rollers of XLRJ.1.1/2' and we trust the information will enable you to proceed with your design. Includes related drawing

Bristol Gas Turbines: Stress Department. Letter from Ransome & Marles Bearing Co. Ltd. Bearings for overspeed generator drive in Olympus 1/2B  PA1716/5/11/2/208  7 July 1952 - 29 July 1952

1 Item

Contents:
5214SR/18. Further to your letter of the 1st inst and subsequent telephone conversation with Mr Stockton, we understand that you now wish to use the inner, cage and rollers of our MRJ.12 instead of LRJ.17and we are therefore enclosing a print giving the necessary information for the 12mm bearing. Includes related drawing and letters

Bristol Gas Turbines: Stress Deprtment. Stress investigation. Olympus Mk.101 generator drive increaser gearbox  PA1716/5/11/2/209  13 January 1953

1 Item

Contents:
5214SR18. Revision of stresses given in 5214SR187 September 1953 for shear neck failure condition. Schemes and drawings used OLS.1793 (B.87250)

Bristol Gas Turbines: Stress Deprtment. Olympus 1/2B generator drive increaser gearbox. Profile diagrams (Issued on MS.1551)  PA1716/5/11/2/210  26 March 1953 - 14 April 1953

1 Item

Bristol Gas Turbines: Stress Department. Stress investigation. Olympus 1/2B generator drive gearbox (increaser)  PA1716/5/11/2/211  19 November 1953

1 Item

Contents:
5214SR/18. Stressing of gear shafts and determining of bearing loads

Bristol Gas Turbines: Stress Department. Stress investigation. Olympus Mk.101 generator drive increaser gearbox  PA1716/5/11/2/212  17 September 1953

1 Item

Contents:
5214SR/18. Stressing of gears, bearings and shafts in generator drive increaser gearbox (in nose bullet)

Bristol Gas Turbines: Stress Department. Stress investigation. Olympus Mk.101 generator drive  PA1716/5/11/2/213  4 December 1953

1 Item

Contents:
5214SR/18. Stressing of shear coupling and drive shaft for P3 generator (6kw) in nose bullet. Drawing used OLS.1626

Bristol Gas Turbines: Stress Department. Design memo GDM/BE.10/129. Olympus 1/2B generator drive 1.35:1 increased gears  PA1716/5/11/2/214  20 August 1952

1 Item

Contents:
5214SR/18. Stress clearance. (a) Normal running 33.5hp at 9870 generator rpm. (b) Shear neck failure 420lb.ft. The bearing arrangement has been examined by the manufacturers and was considered to be satisfactory

Bristol Gas Turbines: Stress Department. Stress summary. Olympus 101, 102 and 104 generator drive  PA1716/5/11/2/215  c. 1952

1 Item

Contents:
5214SR/18. Schemes OLS.1795 (B.75242)

Bristol Aeroplane Co Ltd Stress Department. Static tests on starter drive vertical shafts. Olympus 1/2B 1/2C 100 and 101  PA1716/5/11/2/216  5 June 1953

1 Item

Contents:
5214SR/19

Bristol Aeroplane Co Ltd Stress Department. Static tests on starter drive vertical shafts. Olympus 1/2B 1/2C 100 and 101  PA1716/5/11/2/217  24 November 1954

1 Item

Bristol Aeroplane Co Ltd Mechanical Development - Turbine Engines Department. Failure Report: starter quill shafts and starter to auxiliary drive vertical shaft of Olympus 100  PA1716/5/11/2/218  10 March 1955

1 Item

Bristol Aeroplane Co. Ltd. Stress Department. Olympus 100  PA1716/5/11/2/219/  1955

Bristol Aeroplane Co. Ltd. Stress Department. Memo Particulars of permanent set induced in quill shaft B.47080 (Olympus 100)  PA1716/5/11/2/219/1  18 May 1955

1 Item

Contents:
5214SR/19. Mirrors were used and the telescope stand was set at 5ft 73/4ins from specimen. Both mirrors were set initially at the same scale reading and permanent set was induced so that when all load was removed the scale reading at the stationary end was 69cm and at the moving end was 0cm (at the same height as the specimen). Thus the angle of twist = 1/2 ton -1 69 over 2.54 by 67.75 = 10.9deg (anti-clock). Load required to produce twist = 610lb.ft. (approx)

Bristol Aeroplane Co. Ltd. Stress Department. Olympus 100. Static tests on starter and auxiliary drive vertical shafts B.47080  PA1716/5/11/2/219/2  30 March 1955

1 Item

Contents:
5214SR/19. As a result of overloads on starting, which sheared two starter quill shafts, the vertical shaft was permanently strained. Separate torsional and bending static tests to elastic limit and a final torsional test to destruction have been carried out

Bristol Aeroplane Co. Ltd. Stress Department. Memo to Mr Anthony Inspection Superintendent No.2 factory Sunderland: Particulars of working centre gears (B.71767 B.87256) & (B.71766 B.87258) Olympus 101 Increaser Box Generator drive  PA1716/5/11/2/220  14 December 1953

1 Item

Contents:
5214SR/18. Memo refers to working centre distance for both pairs of gears is 2.773 (see casing drawing B.77846). It then goes on to refer to five drawings for the future

Bristol Aeroplane Co. Ltd. Stress Department. Memo Olympus 101 generator drive profile modification on gear teeth  PA1716/5/11/2/221  9 April 1954

1 Item

Contents:
5214SR/18. From running experience it is apparent that the tip and root relief should be increased. No drawing available

Bristol Aeroplane Co. Ltd. Stress Department. Stress clearance record. Olympus 103 Fuel pump, hyraulic pump, starter, main oil pumps, auxiliary scavenge pump & tachometre, generator drive  PA1716/5/11/2/222  6 February 1956

1 Item

Contents:
5214SR/20. The report goes on to examine the strengths and weaknesses of the above parts. It goes on to give details of the stress cage and torsion factor summaries

Bristol Aeroplane Co. Ltd. Stress Department. Engine stress investigation: Olympus 103, 3 bank auxiliary scavenge pump. Strength of pump (driven gears) spindle  PA1716/5/11/2/223  24 February 1956

1 Item

Contents:
5214SR/20. Contents: calculation of stresses; Conclusion and summary

Bristol Aeroplane Co. Ltd. Stress Department: Stress clearance record. Olympus 103 Basic scheme OLS.3582 Strengthened starter drive  PA1716/5/11/2/224  11 July 1956

1 Item

Contents:
5214SR/20. We have examined scheme OLS.3582 showing the strengthened starter drive quill shaft and find it satisfactory from the stress viewpoint

Bristol Aeroplane Co. Ltd. Stress Department: Engine stress investigation. Olympus Mk.101 starter and accessory drives  PA1716/5/11/2/225  30 November 1956

1 Item

Contents:
5214SR/20. Stresses in bearing housings whenfitted with PH.B liners. Schemes or drawings. Used:OLS.3770; OLS.3667; & OLS.3769. Calculations 1 to 6; Tables of stresses and factors 7

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.104 starter drive, gears & shafts  PA1716/5/11/2/226  30 April 1957

1 Item

Contents:
5214SR/20. Strengthened starter drive with 200lbs.ft shear neck. OLS.3528. Contents: Explanatory notes (Pages 1-3) on use of 200lb.ft shearneck. Routine stressing sheets (pp 4- 13). Summary sheets as follows: Shafts - factor; Serrations - B.pressures; Gears - stresses (pp14 - 17). Gear teeth and serrations added

Bristol Aero-Engines Ltd. Stress Department: Olympus 103 Accessory drive summary  PA1716/5/11/2/227  1957

1 Item

Contents:
5214SR/20. Olympus 103 fuel pump, hydraulic pump, starter; main oil pumps; auxiliary scavenge pump; and tachometre generator drive. Scheme OLS.3381; OLS.3378 (subsid). Arrangement drawings: B.75018 (inner end); B.102407 (Outer end)

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus 102 starter drive, Starter clutch drive  PA1716/5/11/2/228  23 May 1957

1 Item

Contents:
5214SR/20. Torsional stresses, serration bearing pressure, and flexibility calculations. Scheme drawings used: OLS.4078 starter clutch drive with improved flexibility

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus 104 Hyraulic pump drive, quill unit  PA1716/5/11/2/229  11 September 1957

1 Item

Contents:
5214SR/20. Comparison of strengths; sleeve/shear neck. Scheme/drawings used: B.80375 unit; B.54219-20 & B.80376 details

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus 104 & 103 accessory drive summary  PA1716/5/11/2/230  2 May 1956

1 Item

Contents:
5214SR/20. Fuel pumps, hydraulic pump, starter, main oil pumps, auxiliary scavenger pump, & tachometre generator drive. Routine stressing, bearings, gears, serrations, shafts. Routine stressing sheets, tables Pages 1-47; I to XIII inclusive p48; Correction factors p49. Stress summary filed separately under 5214SR/20. Clearance note 5214SR/20. See also 5214SR/20 July 1958

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.104 starter/accessory drives  PA1716/5/11/2/231  July 1958

1 Item

Contents:
5214SR/20. Gears, bearings, shafts etc; Rouine stressing to SM.63. Scheme drawings used: OLS.3378, OLS.3381, OLS.3582, OLS.3834, OLS.3948, OLS.3953. Tables and diagrams to SM.63 Pages 1-66

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.102 starter drive (modified) vertical shaft & spindle  PA1716/5/11/2/232  15 August 1958

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Contents:
5214SR/20. Torsional stresses, serration bearing pressures, and flexibility calculations. Previous calculations 5214SR/20 OLS.54078 dated 25 May 1957. Flexibility of vertical shaft and spindle. Pages 1-2; Routine stressing sheets, tables I, II, VII, VIII, IX, XII; Summary sheets XIV, XVI

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.102 starter drive with 125lbs.ft shear neck  PA1716/5/11/2/233  26 September 1958

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5214SR/20. Scheme drawings B.75018, B.133483. Previous calculations 5214SR/20 dated 2 May 1956 and July 1958. Routine stressing sheets SM.63 1 - 14. Summary sheets 15 - 19

Bristol Aero-Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.101, MK.102, Mk.104 starter drive bevel gears 15T/45T  PA1716/5/11/2/234  12 April 1957

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5214SR/20. Stressing of bevel gears (comparison with existing design) OLS.3953. Table I Case tabulation Page 1; Table XIII clear tooth stresses page 2; Existing starter gears Table XIII clear tooth stresses Page 3

Bristol Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.104  PA1716/5/11/2/235  1959

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Letter from Ransome & Marles bearings Ltd to Bristol Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.104 fuel pump drive  PA1716/5/11/2/235/1  14 July 1959

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5214SR/20. The original fuel pump drive for this engine was cleared by you to our scheme MS.1225. This same drive is now to be modified slightly so that a Dowty fuel pump can be tried on a development engine. Two bearings only are affected; these correspond to positions F and Q respectively on MS.1225. The loads on the remainder of the drive are virtually the same

Bristol Engines Ltd. Stress Department: Engine stress investigation. Olympus Mk.104 Dowty fuel pump drive (alternative to Lucas) with up-speed HP rotor  PA1716/5/11/2/235/2  12 August 1959

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5214SR/20. OLS.4607. Amended to 0354607 14 October 1959. Previous calculations 5214SR/20 starter/accessory drives. Routine stressing and summary. Routine stressing sheets to SM.63 Pages 1-18; Dowty fuel pump powers Page 19

Bristol Engines Ltd. Stress Department: Engine stress investigation. Olympus MK.101, MK.102, Mk.104 generator drive (nose bullet)  PA1716/5/11/2/236  8 December 1959

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5214SR/20. Routine stressing, gears, bearings, shafts, serrations. Scheme B.75242. Previous calculations: 5214SR/18 dated 13 January 1953, and 17 September 1953. Routine stressing sheets pages 1-14; Flexibility of drive Page 15; Strength of planet gears layshaft Page 16

Bristol Engines Ltd. Stress Department: Turbine programme note. B.OL.Mk.102 Static test of starter drive and gear train  PA1716/5/11/2/237  29 November 1956

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5214SR/19. TP.3130. Prior to being used for the engine test programme TP.3095 series, the intermediate casing and associate parts ex OL.102007 (6th build) are to be made available for the test

Tables of Jet Pipe Characteristics  PA1716/5/11/2/238  c. 1950s

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Index to jet pipe characteristics and correspondence regarding static testing of vertical shafts  PA1716/5/11/2/239  1952 - 1954

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Rolls-Royce Industrial & Marine Division Stress Department: Industrial Olympus 'A' rated engines. Failures of turbine blades to Mo3 2345 standards  PA1716/5/11/2/240  31 March 1979

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Engine 200835 at Drax 1005 hours 2nd root seration. Prim Y or SecY 5. Blocked NGV & one CC failed to light. Engine 200627 Drax 609 hours. Top root serration. Prim Y or SecY 5. Displaced NGV. Engine 200602 Ferrybridge 211 hours. Top root serration. Prim Y or SecY 5. Displaced NGV. Engine 200614 Ratcliffe 499 hours Top root serration. Prim Y or SecY 5. Displaced NGV. Engine 200638 Ironbridge 1048 hours. Top root serration. Prim Y or SecY 5. Suspect displaced NGV. Heavy damage. Engine 200814 Drax. 1048 hours. Top root serration. Prim Y or SecY P? No blockage. Being investigated. Engine 200807 Rye House 904 hours. 2nd root serration. Prim Y or SecY 5. 3rd flare break-up. Graph under report showing overall failure rate 7/46.5 or 0.15/1000 hours.

Rolls-Royce (1971) Limited Industrial & Marine Division. Stress Department. Standardisation sheet C. Modification C sheet: HP rotor blade with parrellel shrouds built up with S12 weld deposit. Mod D sheet Approval  PA1716/5/11/2/241  24 December 1976 - 27 April 1977

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Standardisation sheet 6178. Proposed types affected: Olympus 106, 108, 110, 113, 115, 116, 119, 120, 133, 134. To restrict blade untwist and fretting by replacing existing blade, which has a shroud gap of .000/.002 clearance, with interference fitted shroud of .000/.006, and puddle welded shroud abuttment faces of Satellite 12. An overhaul of approx 50% of blades require salvaging. It is considered the introduction of ineterference fitting shrouds will restrict blade vibration, and thus the rate of shroud edge wear, fiving at leat 500 hours in gain life expectancy. Modification D sheet 1 Approval: All the above plus 112, 112/RN.114. To be introduced with future contrscts. Will be available in 8 months. D sheet 2: Additional rework information introduced. Ref IPN 12742/5/C to facilitate early embodiment of the important features of this modification, blades procured to OLP2701 (S.00) can be mixed with blades to this mod standard. The only difference being OLP2701 instructs single pass S12. ten sets of blades to OLP2701 standard are currently available in IMD 75 stores. Mod OLP3411 (Eng). D sheet 3 GAPL section drawing.OLP 3411 (Eng): Schedule 4711007113 turbine Part 1 DIS 106, 113, 116. Schedule 4711006393 turbine Part 1DIS 108, 115. Schedule 4711021345turbine Part 1: DIS 112,112/RN. Schedule 4711023701 turbine Part 1: DIS 114. Schedule 4711008321 turbine Part 1: DIS 110. Schedule 4711040390 turbine Part 1: DIS119, 133. Schedule 4711040633 turbine Part 1: DIS 120, 134. Turbine rotor blade BDA9535 may be reworked to BDD5210 to make BDD5202. Turbine rotor blade BDA9542 may be reworked to BDD5202 standard using Drawing BDD5210.

Rolls-Royce (1971) Limited Industrial & Marine Division. Stress department. Intermal memo: Olympus failure. Disc B409199 Code 115HZ  PA1716/5/11/2/242  1 May 1979

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Ref: WKA/DEJ: This disc was fully machined at Derby and has no connection with any other failure report to date, in that it was produced approximately three years earlier than discs which have been subject of recent investigations. The report covers the three slots identified by Defects Investigation, including Slot 92 where the failure was believed to have occurred. To conclude, it is my opinion that the disc was not responsible for this particular failure.

Rolls-Royce (1971) Limited Industrial & Marine Division.Stress Department. Intermal memo: Engine order excitations due to interference of stator blades and vanes  PA1716/5/11/2/243  2 November 1967

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Ref: JLE/DTL/5/41/72-50-06. Tabulated list of stators etc.

Rolls-Royce (1971) Limited Industrial & Marine Division. Stress Department. Standardisation sheet: Olympus Mk.200 Series and Mk.301. To improve the blade damping and prevent root failures  PA1716/5/11/2/244  17 September 1968

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Drawing Nos.03-4545/-/4. The present standard of Olympus Mk.200 series and Mk.301 HP turbine rotor blades is to modification OLY.1488 standard. To date, there has been a total of 14 blade root failures in Service engines and a further five engines have either suffered blade failures or have been found with cracked roots during acceptance testing or engine repair. Three of the failures were experienced on blades to modification OLY.1488 standard. The failures occurred in the top or second root serrations, usually moleating at the acutely angled trailing edge concave side, or less frequently, at the leading edge convex side of the blade root. This then propogated in fatigue, resulting in fracture across the serrated base section. Tests by IMD indicate a loss of 1/2% thrust. Performance will be checked on first 12 engines

Rolls-Royce (1971) Limited Industrial & Marine Division. Stress Department internal memo: Primary failure of Olympus HP turbine rotor blades in Service  PA1716/5/11/2/245  1968

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Hand-written (in pencil) report from Aero Development Department Parkside. During the period, April 1963 to April 1968, there has been a total of 17 fatigue failures of 1st stage turbine rotor blades in service flight engines. These blades fail at one of three positions: 1 In the aerofoil from approx 1' to 1.25' above the platform. 2 In the top fir tree root serration. 3 In the 2nd fir tree root serration. The instance of these failures in both Mk.200 and Mk.300 series engines is as follows: a) Form failures Mk.200 Mk.300 Form failures 3 1 Top root failures 1 6 2nd root failures 2 4 Total 6 11

Rolls-Royce (1971) Limited Industrial & Marine Division. Stress Department. Olympus 200/300 series engines. 1st stage turbine rotor blade & disc failures  PA1716/5/11/2/246  13 June 1970

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This report gives a complete breakdown of all disc and blade failures up to 1970

Rolls-Royce Limited. Bristol Engine Division. Stress Department. Olympus MK.200/301 Variation of LP/HP RPM over Vulcan Mk.2 flight range  PA1716/5/11/2/247  22 February 1971

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An earlier memo dated 13 June 1968, gavean estimated variation of LP/HP rpm, based on production acceptance figures, altitude effects being determined from early flight testing in the Vulcan aircraft (1962). In order to verify these figures for the latest standard of engine, a flight trial has been carries out on Vulcan XM606 instrumented to record HP rpm over the flight range. The results of these tests (Made on Mk.301 engine ), shows that the altitude effect is not quite as much as originally estimated, and it has been assumed that a similar effect would be applicable to the Mk.201 engine

Rolls-Royce Limited. Bristol Engine Division. Stress Department. HP turbine rotor blade failures  PA1716/5/11/2/248  22 July 1977

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Hand-written report. 1 Thick disc but without differential pitch ie1570 standard. Engine 650224. 17 hours. Top root serration. Engine 650447. 962 hours.Top root serration. Engine 650393. 689 hours. Top rot serration. The failure rate based on the above three failures and 19,620 hours flying before withdrawal of the disc was = 0.152/1000 hours. Thick disc with differential pitch ie 1643 standard. Engine 650039. 813 hours. Top root serration. Engine 620266. 4 hours. Top root serration. On test bed. Engine 650306 1014 hours. Top root serration. Engine 9000003 1660 hours. 2nd root serration (+480 hours in other engine). The failure rate in Service based on the two failures and an estimated 600,000 hours flying Service embodiment of the Mod is = 0.0033/1000 hours. If the test bed failure is included then the rate increases to = 0.005/1000 hours.

Rolls-Royce Limited. Bristol Engine Division Parkside. Stress Department. Olympus Mk.202 & Mk.301 fatigue testing on HP turbine rotor blades  PA1716/5/11/2/249  17 August 1973

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Contract K/47b/65: K/42b/93.Development Engineering Report No.253: Comparative fatigue testing on HP turbine rotor blades machined by BED and Hepworth & Grandage, using HP spool Rig. Engine type HP Spool Rig No.MRE.2: Builds 25, 26 & 27. This report covers a three-part test programme that was arranged following a series of short term HP turbine rotor blade fatigue failures on the latest standard IMD engines. A total of 12 root failures occurred at running times between 156 and 666 hours

Rolls-Royce Limited. Bristol Engine Division Parkside. Stress Department. Special flying instructions/Vulcan/52/Issue 1. Vulcan B2 engine limitations  PA1716/5/11/2/250  4 November 1974

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The continued incidence of Olympus LP turbine blade failures has led to the need for restricted operation in the 95+-1.12% rpm band where resonance and consequent fatigue of the LP blades can occur. In order to minimise the effects of this restriction on the flexibility available to pilots in setting rpm, the existing restricted bands are lifted on engines to post Olympus modification 1570 or 1643 standard. This relaxation has been made possible by the majority of engines in service, now have one or other of the modifications which introduce a stronger HP turbine disc

Rolls-Royce Limited. Bristol Engine Division Parkside. Stress Department. Olympus Mk.301 rotor blade failure at 813 hours  PA1716/5/11/2/251  5 October 1978

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Ref: E/FGPG/JDW/TN. Laboratory Report LE.78/158. This blade had fractured transversely above the top root serration as a result of fatigue cracking which initiated at the concave trailing edge corner of the root. The blade material loading appeared to have been satisfactory. The blade material was found to be metallurgically satisfactory

Rolls-Royce Limited. Aero Division Parkside. Materials Laboratory. Stress Department. Olympus engine 620266 HP turbine blade failure after 4 hours  PA1716/5/11/2/252  12 December 1978

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Ref: E/FGPG/JDW/TN. Laboratory Report LE.78/191. During acceptance testing of engine 620266, fracture of an HP turbine blade root occurred after 4 hours. Subsequent NDT confirmed that two other blades were cracked at the root position. The three blades were submitted to the Laboratory for investigation into the failure. The three failed blades, reference 16, 13 and 8 were identified by the code HWTO. Ten further blades were used in the manufacture of the turbine and these were also obtained for examination

Rolls-Royce Limited. Bristol Engine Division Parkside. Stress Department. Minutes of the meeting held in AQD office Parkside, 8 February 1979, to look into the Olympus disc failure problem  PA1716/5/11/2/253  8 February 1979

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Ref: RH/16/08. Mr Armstrong (the Chairman) reviewed the disc measurement as follows: The disc had ben turned at Dunlop and broached at Derby in 1976. The investigation proved that the correct broach had been used and was not a repeat of the situation in 1973 when 80 discs had been scrapped off. The measurements had shown the throat dimension to be undersize and secondly the across wires dimension was incorrect with shortage of metal on the pressure flanks on one side of the fir tree slot. The amount of error and the position in which it occurred was consistent, with the discrepancy that had been found previously, when the broach has been taken through the same slot twice. The stagger would also be affected

Rolls-Royce Limited. Bristol Engine Division Parkside. Stress Department. Olympus HP turbine rotor blade failures  PA1716/5/11/2/254  1978

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Hand-written un-signed report. 1 Critical rpm band indicated by MES review is 83 - 91% Nh. This is coincides with the IF-6th engine order where the max AR was 55%. 2 The original SF1, which was introduced to avoid the 4th engine order combined disc and blade mode of vibration involving the 'thin' disc, avoided 81-87% LP pm in the case of he Mk.202 engine and 82.5 - 90% LP pm from the Mk.301 engine (ie rpm at 15C deg). 3 The equivalent LP rpm from the HP rpm band given at 0 is as follows:- Mk.202 70-83% LP rpm; Mk.301 69.5-83.5% LP rpm. 4 The failures to date have all been on Mk.301 engines (ie 3 cases in Service) and the bias has always been towards the Mk.30. May be due to more excitation ie higher operating pressure (HOP). 5 Because of 4 it would indicate that the fit of the blades at the root and the outer shroud is not the critical feature leading to the failures, but must be related to the rpm at which the blade is likely to resonate plus the (HOP). 6 Since the recent failures have occurred after the SFI was withdrawn, this also would tend to support comments at 5. 7 Since the likely speed band to avoid is now wider than before (ref 1 and 3) this may lead to compliance problems. Also, most of the band would have been flown in prior to the withdrawal of the SFI and apparently did not produce failures. This would also indicate that the area to worry about is the overlap and this is indicated below: Drawing of Mk.301 showing old SFI and Mk.202 showing new band. The overlap of the Mk.202 is 81-83% LP rpm. The overlap of the Mk.301 is 82.5-83.5% LP rpm. Using the above speed bands the HP rpm. Avoided is 90/91% for the Mk.202 and; is 90.5/91% fo the MK.301. To allow or scatter, the band for both marks could be made 80-85% LP rpm, which would avoid HP rpms between 89/92.5%. It could also be argued that since with the original SFI, there were no failures, that this should be re-introduced. This would encompass the top end of the 6h EO resonance condition covered by the ovelap condition. Olympus engine operation: In circuit 35 67/70% rpm. Approach 75 75-78% rpm. Roller 93% rpm. At below 5,000 not operated between 80-90% LP rpm.

Rolls-Royce (1971) Limited. Bristol Engine Division Parkside. Stress Department. Olympus 301 HP turbine rotor blade failures on 1570 Mod discs fitted with 1643 Mod blades  PA1716/5/11/2/255  17 April 1975

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Report PS276/75. To Jo Pemberton. In view of the failure rate of blades in the Mod.1570 thick discs compared with the original thin discs, an investigation based on dimensional checks has been made. This entailed comparing the slot dimensions of a disc which suffered a blade failure with one without failure. The results including drawings and graphs re. contained in this report

Report from the Ministry of Defence (B409199), to Rolls-Royce (1971) Limited. Bristol Engine Division Parkside. Stress Department. Olympus 301 HP turbine rotor blade failures on 1570 Mod discs fitted with 1643 Mod blades  PA1716/5/11/2/256  22 March 1979

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For the attention of Jo Pemberton: Investigation disc No Code 379. Serial No CJ635. 4 broached slots equi-spaced checked. Number 1 slot taken at random, and numbered in clockwise diection. Details see attached sheets

Rolls-Royce (1971) Limited. Aero Division Ansty. Stress Department. Olympus defect investigation ex engine 650306  PA1716/5/11/2/257  23 April 1979

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Internal memo Superintendent of Metrology, Producer Centre 6 Ref JM/QK

Rolls-Royce Limited. Parkside. Stress Department. Olympus engine 62066 Blade failure in test  PA1716/5/11/2/258  27 April 1979

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Ref RH/16/08. Jo Pemberton Project Engineer AQD, Ansty. Subject to the meeting held 8 February 1979 Ref RH/16/08, report has now been issued by headquarters Quality Engineering

Rolls-Royce Limited. Aero Division, Parkside. Stress Department. Olympus Mk.301 Service engine 650306 rotor blade failure B409197  PA1716/5/11/2/259  8 June 1979

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Laboratory report No. LE/79/120. This turbine blade had failed through the top root serration in the blade form. Photo Fig 1 View of blade fragments. Fig 2 Close-up of root fracture. Photo P6269 close-up of Fig 2. Photo P6270 righr hand side close-up of Fig 2.

Rolls-Royce (1971) Limited. Aero Division, Parkside. Stress Department. Olympus ex engine 900003 blade root failure  PA1716/5/11/2/260  28 June 1979

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Internal memo Superintendent of Metrology, Producer Centre 6 Ref JM/QK. Blade root drawing B409197, cracked blade. Two Photos: 1 P6379 close-up of blade No 29. Photo 2 P6380 close-up of other side

Bristol Aero Engines Ltd Gas turbines. Stress Department. Peliminary report on Olympus Mk.104 turbine blade containment test  PA1716/5/11/2/261  23 July 1958

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Ref: 443C SR/37. The engine, which retained the shroud rings from the previous test, had one of its 2nd stage turbine blades machined in accordance with OLS.4404 Issue 2 (serrations partly removed - the Armstrong Siddeley Motors method), so that it would pull out of the disc

Bristol Aero Engines Ltd Gas turbines. Stress Department. Olympus engine test report  PA1716/5/11/2/262  20 November 1958

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Ref 4434/37. OL TR 2068. Contract No. 13001/KG/M/011/CB12(a) Engine No 101030. Olympus Mk102. Build 11. Turbine containment test

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus engine test report  PA1716/5/11/2/263  20 November 1958

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Ref 4434/37. OL TR 2068. Contract No. 13001/KG/M/011/CB12(a) Engine No 101030. Olympus Mk102. Build 12. Turbine containment test

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus engine stress investigation. Estimation of changes in radial clearance in N labyrinth  PA1716/5/11/2/264  30 August 1957

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Ref: 4434SR/36. Calculation of radial changes in N labyrinth members for Olympus Mk.101, Mk.102 and Mk.104. Calculations attached

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus engine stress investigation. Stresses on Olympus Mk.101 cooled turbine. Front cover plate  PA1716/5/11/2/265  1957

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Ref: 4434/35. Scheme drawings D/OLS3772. OLS4366. Drawing MS2543 of Front diaphragm (cooled turbine). Pages 1- 4 Calculations considering coned portion of cover plate. Page 5: Application of hoop & radial loads on cone to the hub section on Donath Chart. Page 6-9: Deflection due to rotation. Page 10: Rorational stresses on hub from Donath Chart. Investigation of cone under pressure conditions D/OLS/3772

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus engine stress investigation. Stresses on Olympus MK.103 turbine interstage diaphragm  PA1716/5/11/2/266  3 October 1956

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Ref: 4434SR/34. Scheme drawing OLS3560. Page 1 Graph of stresses. Page 3-4 Results from 'deuce'. Page 5 Section details. Page 6-8 Effects of offfset

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus engine stress investigation. Stresses on Olympus MK.104 turbine interstage diaphragm  PA1716/5/11/2/267  February 1959

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Ref: 4434SR/34. Streses in diaphgram with bayonet fixing. Scheme drawings OLS4563. Previous calculations

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus engine stress investigation. Stresses on Olympus MK.101 turbine interstage diaphragm (thickened web)  PA1716/5/11/2/268  8 February 1956

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4434SR/31. Scheme drawings OLS3382. Previous calculations 4444SR/15. Page 1: Individual stresses. Page 2 Total stresses. page tabulated stresses. page 4 Cross sectional view. Page 5 Donath Chart tabulations. Pages 6-7 Themal stresses. Pags 8-10 Spigot loadings. Page 11 Growth at labyrinth diaphgram. Page 12 Pressure differential

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus engine stress investigation. Stresses on Olympus MK.101/2 turbine interstage diaphragm (thickened web). Centrifugal thermal & spigot loading stresses in interstage diphgram  PA1716/5/11/2/269  1 April 1955

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4434SR/29. Scheme or drawings OLS2803. Previous calculaions 4444SR/9 & 4432SR/2. Page 1 Tabulation of stresses. Page 2 drawing GR3703 of interstage diaphgram. Page 3 Graph of interstage diaphragm (thickened web). Page 4 calculations of rotational stresses (no rim load; no side load) Donath Charts. Page 5 Calculation of thermal stresses. Page 6 Estimation of thermal stresses, and stresses due to external loading. Page 7 Side loading 1000lbs/in.

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus MK.101 engine Nos 505 506; MK.102 engine Nos 524 526. N Labyrinth diaphgram to OLS2803  PA1716/5/11/2/270  12 October 1955

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Ref: 4434SR/29. Fretting at bayonets, growth of labyrinth face diameter and inner spiot, and difficulty of removal from 1st stage turbine wheel

Bristol Aero Engines Ltd. Gas turbines, Olympus MK.101  PA1716/5/11/2/271  1955

Bristol Aero Engines Ltd. Gas turbines internal memo. Stress Department. Tolerance of blade slots in turbine wheels Olympus MK.101  PA1716/5/11/2/271/1  4 October 1955

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Ref: 4434SR/27. With reference to your mem CE/EIH/FA/2874 dated 15 September 1955, we agree with the method you propose to adopt in specifying the offset of the blade root CL from the wheel centre. We agree also with the tolerance diameter of 0.020 at the wheelcentre slot

Bristol Aero Engines Ltd. Gas turbines internal memo. Stress Department. Tolerance of blade slots in turbine discs Olympus MK.101  PA1716/5/11/2/271/2  15 September 1955

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Ref: 4434SR/27. Internal memo from Detail DO. We have considered the method of expresssing your recommended tolerances on detail drawings and propose to adopt the method as shown below

Bristol Aero Engines Ltd. Gas turbines internal memo. Stress Department. Turbine wheel root slots Olympus MK.101  PA1716/5/11/2/271/3  9 September 1955

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Ref: 4434SR/27.amined the problem of the tolerances on the offset of the wheel slots on Olympus Mk.101HP & LP wheels and recommend that they be set provisionally (according to the diagram given below) as follows: This memo contains a drawing of the wheel and tolerance tables

Bristol Aero Engines Ltd. Gas turbines. Stress Department. Olympus MK.101 turbine HP & LP wheels  PA1716/5/11/2/271/4  16 September 1955

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Ref: 434SR/27. Tolerance on root fixing slots

Bristol Aeroplane Company Limited. Engine Division. Stress Department. Stresses in the conical flange of Olympus MK.101 turbine shaft B54314  PA1716/5/11/2/272  May 1953

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Ref: 4434SR/25. Photoelestic report PE.142

Bristol Aeroplane Company Limited. Engine Division. Stress Department. Olympus MK.101 turbine disc slot pitch tolerance  PA1716/5/11/2/273  10 January 1956

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Ref: 4434/11.Referring to your note Ref CE/EW-D?CH/2151 dealing with the inspection and detailing of blade roots and slots, it appears that up to a variation in inspection figures obtained by Experimental and Production Department when viewing the same turbine disc, that some looseness is suspected in the dimensioning of the drawing

Bristol Aeroplane Company Limited. Engine Division. Stress Department. Failure of Olympus Mk.101A engine No.520  PA1716/5/11/2/274  22 January 1955

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Ref: 4434SR/11. Notes of a meeting held in Mr Hill's office on Wednesday 19 January 1955 following the failure of Olympus mk.101A engine No.520. The substance of his report indicates the proposed design action to improve the cooling of the 1st and 2nd stage turbine wheels

Bristol Aeroplane Company Limited. Engine Division. Stress Department. Olympus Mk.101 turbine blade roots  PA1716/5/11/2/275  5 March 1954

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Ref: 4434SR/11. The first set of Olympus Mk.101 HP turbine blades on an engine which has run satisfactorily has now been checked in the Bartlett gauge for fir tree root errors. Mr Oliver has confirmed that future blades will have a stagger error between the two sides of the fir tree as recorded by the Bartlett gauge of +0.00025. This figure is considered less than the maximum measured on the set of blades ex Olympus 520

Bristol Aeroplane Company Limited. Development Engineers Department. Stress. Olympus Mk.101/2 engine 503. Rub on 1st stage turbine  PA1716/5/11/2/276  30 January 1951

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Ref: 4434SR/10. After three builds on this engine rubs were found to have occurred between the inner platforms of the first stage turbine stators and the wheel blades. After the first build only, the air baffle attached to the seal ring support cone also rubbed the turbine wheel severely enough to wear through part of the baffle. The total running times on the three builds were 6 hours 49 minutes (18 November 1950 to 23 November 1950); 4 hours (20 December to 21 December 1950) and 2 hours on 7 January 1951

Bristol Aeroplane Company Limited. Mechanical Development Turbine Engines Department. Stress. Olympus Mk.100 engine 507. Failure of 1st stage turbine wheel  PA1716/5/11/2/277  7 May 1956

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Ref: 4434SR/8. Fatigue cracking in the 2nd from bottom root serration of the 1st stage turbine wheel has ocurred on Olympus Mk.100 engine 507, after a running time of 702 hours 46 minutes. This is the first failure of his nature on Olympus Mk.100 engines. The engine failed on 7 January 1956. Failed parts B.62396 1st stage turbine wheel, serial No.396 in H.46 mateial to OLS.745. One blade root slot was cracked in the 2nd from bottom root serration, at the front face acute corne. The crack as due to fatigue which had initiated from a sharp corner formed where the serration corner radius coinsided with the undercut on the front face of the whel rim

Bristol Aeroplane Company Limited. Design memo GDM/BE.10/57. Stress office. Olympus Mk.100/2 Blade locking scheme. Turbine 2nd stage  PA1716/5/11/2/278  28 March 1951

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Ref:4434SR/8. Stress clearance. The above scheme has ben examined and is considered acceptable from the stress point of view. It is estimated that the modification to the blade root decreases its strength by about 7%

Bristol Aeroplane Company Limited. Mechanical Division Turbine Engines Department. Stress. Olympus 100 engine 2602. Fracture of the 1st stage HP turbine disc fitting bolt  PA1716/5/11/2/279  31 March 1954

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Ref:4434SR/5. On the 1st stage turbine fitting bolt, B66567, was found to be fractured in the undercut between the threaded section and parallel section of the bolt

Bristol Aeroplane Company Limited. Olympus Project Engineer. Stress. Failure of a 1st stage disc bolt on Olympus 100 engine 2602  PA1716/5/11/2/280  27 February 1954

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Ref: 4434SR/5. Notes on a meting in Mr Chamberlain's office to discuss the material of the turbine disc bolts, following the failure of a 1st stage disc bolt on Olympus 100 engine 2602. The material specification of the 1st and 2nd stage turbine disc bolts for Olympus 100 and 101 series engines is BACE.236 Issue 1

Bristol Aeroplane Company Limited. Stress Engineer. Olympus 100/2 2nd stage turbine shaft b.37326  PA1716/5/11/2/281  21 April 1952

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Ref: 4434SR/5. It has been bought to our notice that the four air holes drilled in the above shaft are not provided with a blend radius at the intersection of the holes and the wall of the shaft. We would point out that in our assessment of the strength reduction due to holes are suitably radiused. An absence of such radiusing gives rise to a source of weakness in the shaft which becomes considerable in the event of stress fluctuation due to torsial vibration and lateral bending movements

Bristol Aeroplane Company Limited. Engine Stress Investigation. Olympus 1/2 2nd stage turbine shaft B.37326  PA1716/5/11/2/282  16 April 1952

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Ref: 4434SR/5. Investigation into the desirability of radiusing air bleed holes. Contents: 1 Determination of mean clear stress across critical section of hole. Four pages of calculations and drawings

Bristol Aeroplane Company Limited. Engine Stress Investigation. Olympus 1/2 turbine shaft and bolts  PA1716/5/11/2/283  16 May 1950

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Contents:
Ref: 4434/5. Gyro effects and tightening torques. Five pages of calculations and drawings. Includes related addendum

Bristol Aeroplane Company Limited. Engine Stress Investigation. Inspection Department Shop No.4: Slot grading of turbine wheels  PA1716/5/11/2/284  16 August 1950

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Ref: 4434SR/4. Turbine wheels in H.46 and Rex.448 material can be regarded as stable in so far as overspeed testing is concerned, and therefore not subject to changes if the size of the slots alter broaching. Olympus wheels in G.18B can be looked upon in the same light since by the time they are broached they will have been already overspeed tested and therefore, in part finished condition. In the above cases therefore, ie, all wheels in M.46 and Rex.448 and G.18B Olympus only, the grading can be done at the first view after completion of broaching. The aim in this is to enable blade production to proceed without waiting for final completion of the wheels

Bristol Aeroplane Company Limited. Engine Stress Investigation bearings. BE.10 engine. Preliminary bearing loads  PA1716/5/11/2/285  27 September 1948

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Contents:
Ref: 45SR/6. CE/SWM/47425.Bearings numbered 1 to 7 from front to rear

Bristol Aeroplane Company Limited. Engine Stress Investigation bearings. BE.10 engine. Preliminary bearing loads  PA1716/5/11/2/286  1 November 1948

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Contents:
Ref: 45SR/6. CE/SWM/47425. Issue 2/2. Bearings numbered 1 to 7 from front to rear

Bristol Aeroplane Company Limited. Engine Stress Investigation bearings. Bearing test rig requirements BE.10 etc engine bearings  PA1716/5/11/2/287  2 December 1948

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Contents:
Ref: 45SR/6. CE/ SWM/E/51393. Drawing ES.999 Issue C, mentioned are not in our possession, nor any other drawing in this report

Bristol Aeroplane Company Limited. Engine Stress Investigation bearings. Olympus bearing test requirements  PA1716/5/11/2/288  20 December 1948

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Contents:
Ref: 45SR/6. CE/HCM/S/51928/S

Bristol Aeroplane Company Limited. Engine Stress Investigation bearings. BE.10 no.2 bearing load. LP compressor rotor PAN - 105  PA1716/5/11/2/289  23 December 1948

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Contents:
Ref: 45SR/6. P/U.10/G/2. The necessesity of pressurising the compartment forward of the LP compressor, in order to reduce the thrust loading on the bearing, has been investigated for maximum RPM, ICAN, static, and 600 mph, Arctic conditions

Bristol Aeroplane Company Limited. Engine Stress Investigation Office memo. bearings: BE.10 engine centre-line bearing  PA1716/5/11/2/290  30 December 1948

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Contents:
Ref: 45SR/6. CE/SWM/E/53924. We do not have the drawing mentioned

Bristol Aeroplane Company Limited. Engine Stress Investigation Office memo. bearings: BE.10 engine No.4 bearing load. PAN - 107  PA1716/5/11/2/291  4 January 1949

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Ref: 45SR/6. P/U.10/G/3. A means of maintaining the above bearing load within permissible limits, without resorting to pressure balancing on the HP compressor, has been devised as follows: Three labyrinths to be provided at the rear of the HP compressor, having diametres of 22', 17' and 7' approximately. Each of the two labyrinth chambers so formed to be vented to atmosphere via passages of not less than 3.0 sq ins, with blow-off vents opening at 70lb sq in. also located in the vent(s) from the outer chamber (ie between the 22' and 17' dia labyrinths). The table below summarises the required dimensions for the larger diametere labyrinths. This report is in very poor condition and must be handled extremely carefully

Bristol Aeroplane Company Limited. Engine Stress Investigation Office memo. bearings: BE.10 engine No.4 bearing load. PAN - 107  PA1716/5/11/2/292  4 January 1949

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Contents:
Ref: 45SR/6. P/U.10/G/3. A means of maintaining the above bearing load within permissible limits, without resorting to pressure balancing on the HP compressor, has been devised as follows: Three labyrinths to be provided at the rear of the HP compressor, having diametres of 22', 17' and 7' approximately. Each of the two labyrinth chambrs so formed to be vented to atmosphere via passages of not less than 3.0 sq ins, with blow-off vents opening at 70lb sq in. also located in the vent(s) from the outer chamber (ie between the 22' and 17' dia labyrinths). The table below summarises the required dimensions for the larger diameter labyrinths. This report is ia properly typed report of the previous record

Bristol Aeroplane Company Limited. Dvelopment Department (Turbines). Engine Stress Investigation. Bearings: Bearing test rig requirements for BE.10 etc. bearings  PA1716/5/11/2/293  10 January 1949

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Ref: 45SR/6. CE/JC/CAG/54322. It is agreed that a programme of bearing development rig testing is to be initiated and continue for Olympus bearings in the Mechanical Rig Shop in the same manner as for Proteus and Theseus bearings

Bristol Aeroplane Company Limited. Engine Stress Investigation. Bearings: BE.10 high-pressure compressor. Temperature and pressure through the compressor. ICAN, SL Static  PA1716/5/11/2/294  27 January 1949

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Contents:
Ref: 45SR/6. TED.113. Report

Letter from Ransome & Marles (bearing manufacturers) to Bristol Aeroplane Company Limited. Engine Stress Investigation. bearings: BE.10 engine centre-line bearings  PA1716/5/11/2/295  17 February 1949

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Contents:
Your ref: 45SR/6. CE/SWM/E/53924. We have now finalised our consideration of the bearings for the above application as shown on your drawing MS.999 Issue D and give below our comments on the various bearings

Bristol Aeroplane Company Limited. Engine Stress Investigation. Bearings: BE.10 engine No.4 bearing load PAN-117 (superceding PAN-107)  PA1716/5/11/2/296  7 April 1949

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Contents:
Ref: 45SR/6. CE/SWM/E CEB. The pincipals of the design described in PAN-107 are adhered to, but various dimensional changes have been found necessary since the date of the previous note, in order to ensure that the labyrinth blow-off valve closes before 20,000ft, altitude is reached, to restrict oil leakage from No.4 bearing, and to meet the bearing load limitations

Bristol Aeroplane Company Limited. Plant Design Office. Engine Stress Investigation. bearings: Bearing tests. Olympus  PA1716/5/11/2/297  8 April 1949

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Ref: 45SR/6. EW/TPD/DD/MB/25. A test assembly in connection with scheme SCG.645 (No.4 bearing) which will cater for radial loads in addition to the thrust load previously mentioned. The normal radial loading device is capable of applying a maximum of 5,000lbs per stacked test pair and this will, no doubt, be adequate for your requirements

Bristol Aeroplane Company Limited. Plant Design Office. Engine Stress Investigation. Bearings: Bearing tests. Olympus  PA1716/5/11/2/298  8 April 1949

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Contents:
Ref: 45SR/6. EW/TPD/DD/MB/25. The recipiant of this report has underlined the following: gyroscopic action in flight will apply radial loads considerably in excess of those previously envisaged

Bristol Aeroplane Company Limited. Plant Design Office. Engine Stress Investigation. Bearings: Bearing tests. Olympus  PA1716/5/11/2/299  27 April 1949

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Ref: 45SR/6. CE/SWM/WC/60828. Par 3: It is to be noted, that the first tests to be carried out will be the thrust balancing device tests as outlined on SCG.645, and furthermore the parts cleared by the department necessary for such test have been completed since 15 February 1949. Consquently as soon as the parts put in hand by your department become available, testing will commence

Bristol Aeroplane Company Limited. Technical Supply Engineer's Department. Engine Stress Investigation. Bearings: List of Olympus bearings in hand up to 12 May 1949  PA1716/5/11/2/300  12 May 1949

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Contents:
Ref: 45SR/6. CE/F/G/61457

Bristol Aeroplane Company Limited. Engine Stress Investigation. Bearings: Olympus oil supply to main bearings  PA1716/5/11/2/301  18 May 1949

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Contents:
Ref: 45SR/6

Bristol Aeroplane Company Limited. Engine Stress Investigation. Bearings: Olympus journal loads on main bearings  PA1716/5/11/2/302  19 May 1949

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Contents:
Ref: 45SR/6

Letter from Ransome & Marles (bearing manufacturer) to Bristol Aeroplane Company Limited. Engine Stress Investigation. Bearings: Bearing applications on the Olympus engine  PA1716/5/11/2/303  1 June 1949

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Contents:
Ref: 45SR/6. Forthcoming visit to Bristol to discuss the outstanding bearing problem on the Olympus

Letter to Ransome & Marles (bearing manufacturer) from Bristol Aeroplane Company Limited. Engine Stress Investigation. Bearings: Bearing applications on the Olympus engine  PA1716/5/11/2/304  8 June 1949

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Contents:
Ref: 45SR/6. Proposed visit of Messers Storer and Rutherford to Bristol aeroplane Company to discuss Olympus bearings

Bristol Aeroplane Company Limited. Engine Stress Investigation. Olympus engine bearing loads  PA1716/5/11/2/305  9 June 1949

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Contents:
Ref: 45SR/6. CE/SWM/47425. Issue.3. Bearings numbered 1 to 8 from front to rear

Bristol Aeroplane Company Limited. Engine Stress Investigation. Outstanding Olympus engine bearings  PA1716/5/11/2/306  1 June 1949

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Contents:
Ref: 45SR/6. Telephone conversation re. proposed visit of Messers Messers Storer & Rutherford to Bristol Aeroplane Company re. Outstanding order for Olympus bearings

Bristol Aeroplane Company Limited. Plant Design Office memo. Engine Stress Investigation. Bearing test rig No.2 Olympus tests  PA1716/5/11/2/307  23 June 1949

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Contents:
Ref: 45SR/6. RW/TPD/DD/M/79. Since receipt of our memo of 10 January 1949, a complete redesign of Olympus bearings has taken place and the design of test assemblies has consequently been held up. I have now obtained a print of MS.1054, which supercedes MS.999, and gives particulars of the redesigned bearings. Design of the test assemblies can now proceed. It has been agreed that bearings Nos.2 4, and 8 positions will be tested and first priority will be the No.2 stacked pair with thrust balance device. Existing assembly RM.999 will cover the No.8 position. The shaft for the No.2 position will probably suit the No.4 position when fitted with adaptor sleeves etc.

Bristol Aeroplane Company Limited. Plant Design Office memo. Engine Stress Investigation. Bearing test rig No.1 Olympus tests  PA1716/5/11/2/308  23 June 1949

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Contents:
Ref: 45SR/6. EW/TPD/DD/MF. Para 4: Radial and thrust loading devices will be applicable in all three cases and it should be noted that the maximum capacity of the existing rig is:- Total thrust load 15,000lbs. Total radial load 10,000lbs.

Bristol Aeroplane Company Limited. Technical Supply Engineer's Department memo. Engine Stress Investigation. Olympus ball and roller bearings  PA1716/5/11/2/309  28 June 1949

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Contents:
Ref: 45SR/6. CF/F/G/65081. Attached are two pages of all Olympus ball and roller bearings that have been ordered up to and including 29 June 1949

Bristol Aeroplane Company Limited. Engine Stress Investigation. Report on liason with Ransome & Marles to clear Olympus centre-line bearings  PA1716/5/11/2/310  13 July 1949

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Contents:
Ref: 45SR/6. This is a hand-written report which goes into details of the affair, however, it is unsigned

Bristol Aeroplane Company Limited. Engine Design memo. Engine Stress Investigation. Olympus ball and roller bearings  PA1716/5/11/2/311  14 July 1949

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Contents:
Ref: 45SR/6. CE/SWM/WC/6577. The position regarding Olympus bearings has now been clarified, and as a result, does not line up with your list issued on 28 June 1949 ref: CE/F/g?65081, and for your information we have prepared lists showing the bearings now cleared under the various schemes, from which you will be able to amend the respective assemblies as follows:- Oil sump delivery assembly No.302. Compressor rotor assembly No.304. Starter drive assembly No.314. Fuel pump drive assembly No.321 etc.

Letter to Ransome & Marles (bearing manufacturers) from Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus No.5 bearing  PA1716/5/11/2/312  8 August 1949

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Contents:
Ref: 45SR/6. CE/SWM/E/66938. We enclose herewith a copy of our Design Scheme OLS.216, showing our latest proposals for the above bearing, which we are specifying in tungsten-chrome steel, fitted with a granodised steel cage and made to precision limits of accuracy. The loads and running conditions will be as shown on our Scheme MS.1054, already in your possession. We shall be pleased to receive our comments on the above and a copy of your preliminary data-sheet. A modified copy of our Scheme MS.1054 will be forwarded to you in due course

Letter from Ransome & Marles (bearing manufacturers) to Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus No.5 bearing  PA1716/5/11/2/313  23 August 1949

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Contents:
Ref: 45SR/6. CE/SWM/E/69201. It will be noted that we propose to supply the bearing with a convex outer track and a diametrical clearance of .0045' to .005.' This we think should be adequate if the temperatures given in your earlier scheme are likely to be retained

Letter to Ransome & Marles (bearing manufacturers) from Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Bearings for Olympus engines  PA1716/5/11/2/314  3 October 1949

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Contents:
Ref: 45SR/6. CE/SWM/E/69201. You will notice that some of the bearing race temperatures have been modified; this has been done to bring them into line with your latest temperature estimations. Attached, hand-written note of questions: What are changes introduced by his (as distinct from bringing records into line with revisions already notified to R & Ms). Temperature changes and insignificant rounding-off of load figures

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus centre-line bearings  PA1716/5/11/2/315  12 October 1949

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Contents:
Ref: 45SR/6. CE/SWM/E/71021. Scheme MS.1054 Issue B, which gives the latest particulars and running condition to the above bearings. This scheme superedes MS.1054 Issue A, any copies of which should be destroyed

Letter from Ransome & Marles (bearing manufacturers) to Bristol Aeroplane Company Limited. Engine Division. Engine Stress Investigation. Bearings for Olympus engine  PA1716/5/11/2/316  14 October 1949

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Contents:
Your Ref: 45SR/6. CE/SWM/E/69201. Thank you for supplying a copy of Scheme MS.1054 Issue B, giving up to date particulars of the runnng conditions for the bearing as above. In view of the revised temperature figures, we would suggest that the diametrical clearance should be increased on No.5 bearing your part No. B.29579 to .0055' to .006', this will bring it into line with the fit of the outer bearings and take into account the increased temperature

Letter to Ransome & Marles (bearing manufacturers) from Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Bearings for Olympus engine  PA1716/5/11/2/317  20 October 1949 - 21 October 1949

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Contents:
Ref: 5SR/6. CE/SWM/E/71641. We are accepting your recommendation to increase the diameter-clearance of No.5 bearing

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Bearings. Velocities in oil-delivery jets for Olympus No.2 bearing  PA1716/5/11/2/318  7 December 1949

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Contents:
Ref: 45SR/6. List of tables

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Bearings. Velocities in oil-delivery jets for Olympus No.2 bearing  PA1716/5/11/2/319  7 December 1949

Contents:
Ref:45SR/6. list of velocities

Letter to Hoffman Manufacturing Co (manufacturer of bearings) from Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Bearings. Olympus Mk.1/2 bearings  PA1716/5/11/2/320  28 February 1951

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Contents:
Ref: 45SR/6. DCE/RCF/272. We should b glad to know your delivery promises for the main shaft bearings for which you have not already quoted

Bristol Aeroplane Company Limited. Stress Office memo. Engine Stress Investigation. Bearings. Olympus main bearing thrust loads  PA1716/5/11/2/321  21 April 1950

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Contents:
Ref: 45SR/6.DCE/SWM/KC/10. In connection with the first test run of the Olympus, Messers Ransome & Marles have brought to our notice that the thust bearings at positions No.2, 4 and 8 will fail if the thrust load is less than the radial load. As it is poposed to 'run-in' the first engine at a low rpm, we would like to know the thust loads which will be imposed on the aformentioned bearings, for a range of speeds up to 4,000 pm (LP compressor), in order that we may advise the test engineers regarding suitable speeds

Bristol Aeroplane Company Limited. Turbine Design Drawing Office. Engine Stress Investigation. Bearings. Olympus main shaft bearings  PA1716/5/11/2/322  8 May 1950

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Contents:
Ref: 5SR/6. DCE/FCM/EB. Recent changes in concessions have been made to the main shaft bearings for Olympus engines, and in order that the position may be claified, we give the following list showing part numbers, with any alterations which may be used on the first engines

Letter to Ransome & Marles (bearing manufacturers) from Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Preliminary engine test report B.OL.1 Engine No.501 Build 1  PA1716/5/11/2/323  15 June 1950

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Contents:
Ref: 45SR/6. TPR.8002. Lighting up tests were carried out successfully and a good start with little flame was obtained by motoring up to 600 rear com rpm; lighting up and then motoring up to full speed on the starter rotor. The maximum jet pipe temperature recorded during this start was 400degC

Letter from Ransome & Marles (bearing manufacturers) to Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Preliminary engine test report B.OL.1 Engine No.501 Build 1  PA1716/5/11/2/324  19 June 1950

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Contents:
Ref: 45SR/6. DCE/SWM/KC/135. We thank you for your letter of the 7th inst and closing a copy of Scheme MS.1154 showing a proposed bearing arrangement for the above application. We do not approve of the proposal to make the inner race integral with the gear. This makes a very complicated component which would be unnecessarily difficult to manufacture. We note that you suggest a material similar to DTD.551 Nitrided but would point out that we understand that this material has failed quickly in the test bearing which you have recently tried and we therefore doubt whether it is suitable material for producing bearing races. We would strongly advise you to use a bearing of standard shape and we feel that by a slight re-design around this postion of the job, you could accommodate our XLRJ.4'E, the overall dimensions of which are 4'by 5.5/8' by 7/8' and we would most strongly recommend you adopt this course

Telephone to Ransome & Marles (bearing manufacturers) from Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. OLympus Mk.2 No.8 bearing  PA1716/5/11/2/325  7 July 1950

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Contents:
Ref: 45SR/6. Mr Rutherford (Ransome & Marles) confirmed that the above bearing as shown on the peliminary scheme handed to him on 28 June, would be satisfactory

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus-2 G Labyrinth PAN-139  PA1716/5/11/2/326  16 October 1950

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Contents:
Ref: 45SR/6. DCE/SWM/KC/CEB. Following the attention made to N labyrinth on the HP turbine, the diameter of G labyrinth can be reduced

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus-2 C Labyrinth PAN-140  PA1716/5/11/2/327  25 October 1950

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Contents:
Ref: 45SR/6.DCE/SWM/KC/CEB. Due to changes in design it has now been found possible to reduce the diameter of the C labyrinth

Letter from Hoffman manufacturing Co Ltd (Bearing manufacturers) to Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus MK.1/2 bearings  PA1716/5/11/2/328  23 October 1950

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Contents:
Ref: 45SR/6. I promised to send you particulars of our Olympus bearings in order that you could put up proposals for Hoffman alternatives. These bearings fall into two general classes 1 Main shaft bearings; 2 Accessory drive bearings, all have steel cages. I am, therefore, attaching copies of drawings which have been prepared by Mr Chamberlaine, giving 1 general arrangements of each bearing, together with the operating conditions, and 2 Detailed drawings of existing bearings, where they would be required by you for information on overall dimensions

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus IV HP compressor rotor blades. Stress in rotor blades  PA1716/5/11/2/329  25 May 1951

Contents:
Ref: 4366SR/3. Contents. Pages 1-3 calculations. Page 4 Graph axial gas loading. page 5 Tangental gas loading. Page 6 to end calculations

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus 4 LP compressor (enlarged annulus) Re-stressing of rotor blades due to enlarged annulus  PA1716/5/11/2/330  8 August 1952

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Contents:
Ref: 4366/2. Pages 1-3 calculations. Page 4 Enlarged annulus area; tangental gas loading. Page 5 Enlarged annulus area, axial gas loading. Pages 6-25 calculations

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus 6D LP compressor. Rotor blade root fixings  PA1716/5/11/2/331  1953

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Contents:
Ref: 4366/2. Stresses in blade root fixings including gas bending effects and stresses in 5th stage disc lobe including asymmetric loading effect. Contents: 4 pages of calculations and drawings

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus Mk.4 LP compressor. Rotor blade root fixing stresses  PA1716/5/11/2/332  17 April 1953

Contents:
Ref: 4366/2.Pages 1-13 calculations and tables

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus Mk.IV LP compressor. Rotor blade root fixings  PA1716/5/11/2/333  16 July 1953

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Contents:
Ref: 4366/3. Proposed new root fixing broach. Previous calculations 4366/3. Contents: Pages 1-9 calculations and drawings

Bristol Aeroplane Company Limited. Stress Office. Engine Stress Investigation. Olympus Mk.IV LP compressor. Rotor blade root fixings  PA1716/5/11/2/334  17 July 1953

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Contents:
Ref: 4366/2.Proposed new root fixing broach. Previous calculations 4366/2. Contents: Pages 1-7 Calculations and drawings

Bristol Aeroplane Company Limited. Stress Office. Failure report. Engine Stress report: Olympus Mk.IV LP Rotor blade root fixings  PA1716/5/11/2/335  27 July 1953

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Contents:
Ref: 4366SR/2. Recent fatigue cracking of Proteus III fir stress disc lobes, resulting in one case in complete fracture of the lobes and consequent destruction of the compressor, indicate that the fillet stresses in the disc lobes are too high to give extended disc life. Calculations of these fillet stresses is complicated by the presence of interminate vibration loads, the value of which can only be properly obtained by running experience

Bristol Aeroplane Company Limited. Stress Office. Engine Stress investigation: Olympus Mk.IV HP Rotor blade roots  PA1716/5/11/2/336  17 August 1953

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Contents:
Ref: 4366/3. Effect on root stresses increasing root width by 0.50'(using oversize broach). Contents: One page of tables

Bristol Aeroplane Company Limited. Stress Office. Engine Stress investigation: Olympus Mk.IV LP Compressor rotor blade tip clearances  PA1716/5/11/2/337  23 October 1953

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Contents:
Ref: 4366/2. Performance calculations rederred to: 4366/2 & 4356/2. Contents: Page 1 Summary. Pages 2-3 calculations

Bristol Aeroplane Company Limited. Stress Office. Failure report. Engine Stress report: Olympus Mk.IV LP rotor blade root fixings  PA1716/5/11/2/338  27 July 1953

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Contents:
Ref: 4366SR/2. Recent fatigue cracking of Proteus III fir tree lobes, resulting in one case in complete destruction of the compressor

Bristol Aeroplane Company Limited. Stress Office. Failure report. Engine Stress report: Olympus Mk.IV HP compressor rotor blade tip clearance  PA1716/5/11/2/339  23 October 1953

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Contents:
Ref: 4366/3. Calculationa DJ Fortune. Performance office data used PDM.41. Previous calculations referred to 4366/3 & 4356/3

Bristol Aeroplane Company Limited. Stress Office. Failure report. Engine Stress report: Olympus Mk.IV LP compressor 1st stage rotor blade  PA1716/5/11/2/340  13 November 1953

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Contents:
Ref: 4366SR/2. Calculation RE Jenkins. Performance office data used GP/7 6896SR/2. Previous calculations referred to 4363SR/7. Olympus IV factors to be applied to blade stresses for different engine conditions. Reference GP/7 BOL.4 internal engine conditions and memo from P and A department giving Mach 2 internal engine conditions. dated 22 October 1953. Table listed below gives a breakdown of engine conditions at various speeds

Bristol Aeroplane Company Limited. Stress Office. Engine Stress clearance report: Olympus Mk.IV HP compressor rotor blades and root fixing  PA1716/5/11/2/341  8 December 1953

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Contents:
Ref: 4366/3. This note gives general stress clearance to the HP rotor blades with section data as shown on 03S 131-4, Ref PDM.41, for the following flight conditions

Bristol Aeroplane Company Limited. Stress Office. Engine Stress clearance report: Olympus Mk.IV LP compressor rotor blades and root fixing  PA1716/5/11/2/342  8 December 1953

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Contents:
Ref:4366/2. This note gives general stress clearance to the LP rotor blades with section data as shown on 03S 241-4 Ref GN.593 PDM.42 & 114, for the following flight conditions: 1 ICAN Sea level static 2 ICAN Sea level 600 knots 3 -25deg.C Sea level 557 knots 4+25deg.C Sea level 630 knots 5 ICAN Sea level Tropopaue 500 knots Material should be BACE 245

Bristol Aeroplane Company Limited. Stress Office. Engine Stress investigation report: Olympus 6 LP compressor rotor blades  PA1716/5/11/2/343  16 March 1954

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Contents:
Ref: 4366/2. Scheme or drawing used PDM.220. Stresses in BOR.6 & all rotor blades. Blades physically as BOL.4 but with increased t/c tapering from 12% at the root to 5% at the tip

Bristol Aeroplane Company Limited. Stress Department Engine Stress investigation report: Olympus 4 development. LP compressor rotor blades  PA1716/5/11/2/344  10 February 1954

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Contents:
Ref: 4366SR/2.BY KR Chamberlain. The enclosed tabulation gives stresses in the rotor blades for the design speed 6320rmp and for the 5% & 16% up-speed cases, also the adjustments to the blades considered necessary to give stress clearance for these latter cases

Bristol Aeroplane Company Limited. Performance & Aerodynamics Department. Engine Stress investigation report: B01.6 LP compressor 1st stage rotor blades stresses  PA1716/5/11/2/345  19 March 1954

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Contents:
Ref: 4366SR/2. GN 896

Bristol Aeroplane Company Limited. Stress Department: Notes on meeting to discuss Olympus 6 compressor & turbine rotor blade roots  PA1716/5/11/2/346  26 April 1954

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Contents:
Ref: 4366SR/2. This meeting was held primarily to review the proportions of the blade roots on the Olympus 4 - 6 LP compressor. These have been criticised in view of the apparent excessive depth of serration in comparison with the thickness at the neck of the blade root

Bristol Aeroplane Company Limited. Stress Department: Olympus 6 LP compressor rotor blade roots  PA1716/5/11/2/347  13 May 1954

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Contents:
Ref: 4366SR/2. An investigation has been made into the use of the blade root form standardised for BE.25 and BE.26 engines, with the aluminium alloy compressor blades for the Olympus 6 engine

Bristol Aeroplane Company Limited. Stress Department. Engine stress investigation: Olympus 6 LP compressor root fixings  PA1716/5/11/2/348  c. 1954

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Contents:
Ref: 4366/2. Oversize broaches for LP discs

Bristol Aeroplane Company Limited. Stress Department.Engine stress investigation: Olympus 6 LP compressor rotor blades.  PA1716/5/11/2/349  29 June 1954

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Contents:
Ref: 4366/2.By RSL Pritchard. Stresses in Olympus 6 LP compressor rotor blades under various aerobatic conditions. Previous calculations referred to 4316/2, 4366SR/2, 8 August 1952. Contents Page 1 summary; Evaluation of factors for the engine conditions pages 2 & 3; data given Page 3; Calculation of correction factors pages 4-8

Bristol Aeroplane Company Limited. Engineering Department. Engine stress investigation: Olympus Mk.6D development. LP 1st stage rotor blades in BASE308  PA1716/5/11/2/350  5 October 1954

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Contents:
Ref: 4366/12. Cancellation of LP 1st stage rotor blades ordered on 03N.316. The order for the two sets of HP 1st stage rotor blades in BASE308 are to stand

Bristol Aeroplane Company Limited. Stress Department. Engine stress investigation: Olympus Mk.6. LP compressor rotor blades root fixing  PA1716/5/11/2/351  22 October 1954

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Ref: 4366/2. DH hughes & R Pritchard. Stresses of root fixings with 101 type roots. Note: The rim shapes are those of B 01.6D. Scheme or drawings used: 03S 273/14-13

Bristol Aeroplane Company Limited. Mechanical Development Turbine Engines Department. Engine stress investigation: Minutes of meeting held to discuss matters concerning Olympus Mk.6.D. Engines Nos.601 & 602  PA1716/5/11/2/352  3 November 1954

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Ref: 4366/2. A report of the primary total failures on B 0L.601 was first given, this was the same as was reported in report ref CE/RCP/PJEH/18094 with no further additions. The results of fatigue tests on 4th stage blades show them to be weak in 2nd flap vibration which leads to the conclusion that the most probable cause of failure is 2nd flap vibration excited by 8 intermediate vanes at 5730 rpm, for the 4th stage blades. Because of exceptionally high resonance on the 4th stage blades it is quite reasonable to believe that the 5th stage blades failed off resonance, thus the blade is very critical

Bristol Aeroplane Company Limited. Stress Department. Engine stress investigation: Olympus Mk.6 LP compressor  PA1716/5/11/2/353  1955

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Bristol Aeroplane Company Limited. Stress Department. Engine stress investigation: Olympus Mk.6 LP compressor rotor  PA1716/5/11/2/353/1  17 March 1955

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Ref: 4366/5. Stresses in redesigned 4th & 5th stage LP rotor blades under various aerobatic conditions. Performance office data used: PDMs 318 & 332. TED.4727. Previous calculations referred to: 4366/2 (29 June 1954)

Bristol Aeroplane Company Limited. Stress Department. Engine stress investigation: Olympus Mk.6 LP compressor 4th & 5th stage root fixing  PA1716/5/11/2/353/2  22 March 1955

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4366/2. Stressing of root fixings on redesigned 4th & 5th stage lP compressor rotor blades. Schemes or drawings used: 035 273/13. Previous calculations referred to: 4366/2 22 October 1954

Bristol Aeroplane Company Limited. Mechanical DevelopmentTurbine engines Department: Meeting held to discuss LP compressor failure on Olympus 6D engine No. 604 on Friday 29 APril 1955  PA1716/5/11/2/354  3 May 1955

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Ref: 4366SR/5. The failure was analysed as follows: 1 Fatigue failure of four 1st stage blades; two blades had fractured through the top root serration; one blade was cracked in the top serration and one cracked in the bottom serration. One fractured blade had fatigued over about one-third of the area of the top serration. 2 Fatigue failures of three 2nd stage blades, one blade had fractured through the top root serration and was also cracked in the bottom serration

Bristol Aeroplane Company Limited. Stress Office. Olympus 6 LP compressor 5th stage rotor blade  PA1716/5/11/2/355  1 July 1955

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Contents:
Ref: 44366SR/5. Failure of the 5th blade roots and cracking of the serrated disc rim due to fatigue, derived from running at resonant conditions under a powerful excitation, is probably aggravated by local stresses arising from certain design features

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Olympus Mk.4 components. LP compressor research & routine dummy blade weights  PA1716/5/11/2/356  30 April 1953

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Ref: 4096SR/4. It should be noted that the Allen screw locking device applies only to the 2nd stage dummy weight, the positive location of which is necessary when overspeeding the 1st and 2nd stage rotor assembly alone

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Research programme No. 1817. Olympus overspeed rig: B.0L.4  PA1716/5/11/2/357  18 June 1953

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Ref: 4096SR/4. The following overspeed assemblies are to be manufacured for test on the above rig: 1 B.01.4 1st & 2nd stage LP rotor assembly (minus blades). 2 B.01.4 1st & 2nd stage HP rotor assembly (minus blades). 3 Suitable dummy blade weights for these units are to be designed by the Stress Office.

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Acceptance overspeed tests on Olympus 4 components, LP compressor assembly  PA1716/5/11/2/358  25 June 1953

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Ref: 4096SR/4. It should only be necessary to overspeed the first of these rotors. The balanced compressor assembly, complete with dummy blade weights to DT.291567-71 is to be overspeeded in the following manner. 1 Measure the outside diameter at four equally spaced stations around the predetermined circumference on the 1st, 3rd & 5th stage discs. Note the room temperatures. 2 Set probes over the following to a clearance of 0.040. i) 1st stage dummy blade weight. ii) Spacing ring between 3rd & 4th stage blade weights. iii) 3rd stage dummy blade weight. iv) 5th stage dummy blade weight.

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Overspeeding Olympus Mk.4 components; 1st & 2nd stage LP coned compressor rotor assembly. Fitted with dummy blade weights  PA1716/5/11/2/359  27 July 1953

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Ref: 4096SR/4. In view of the high loads which will be imposed on the bolts connecting the 1st & 2nd stage rotor discs to the rotor centre, it is necessary to carry out initial tests as soon as possible to ascertain the reserve factor of the bolts under static and dynamic conditions and the behaviour of the coned rotor assembly.

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Overspeeding Olympus Mk.4 components; 1st & 2nd stage coned rotor asemblies for LP & HP compressors  PA1716/5/11/2/360  27 July 1953

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Ref: 4096SR/4. We have examined your scheme RL.19824 showing the arrangement for overspeeding the HP & LP Olympus Mk.4 1st & 2nd stage compressor rotor assemblies. Incorporating our suggestions to make the respective rotor centres of the same material and as dimensionally similar to engine components we find this arrangement satisfactory. This is a memo from the Stress department to Mr Stevenson Engineering

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Overspeeding Olympus Mk.4 components; 1st & 2nd stage coned assembly  PA1716/5/11/2/361  2 December 1953

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Ref: 4096SR/4. Since the behaviour, under running conditions of dummy blade weights retained by Allen type screws in a tapering root slot as present in the 2nd stage disc, in unknown, it is thought desirable to safeguard against axial movement of the weights, should the nip caused by the screw due to be lost due to rim expansion

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Overspeeding Olympus Mk.4 components; 1st & 2nd stage LP coned compressor rotor assembly. Issue 2.  PA1716/5/11/2/362  1 December 1953

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Contents:
Ref: 4096SR/4. In view of the high loads which will be imposed on the bolts connecting the 1st & 2nd stage rotor discs to the rotor centre, it is necessary to carry out initial tests as soon as possible to ascertain the reserve factor of the bolts under static and dynamic conditions and the behaviour of the coned rotor assembly

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Olympus Overspeed rig: B.01.4 LP 1st & 2nd stage rotor assemblies. Scheme SCS.1483 Issue 2  PA1716/5/11/2/363  2 December 1953

Contents:
Ref: 4096SR/4. In order to prevent the 2nd stage dummy blade weights from moving axially, a locking ring B.88789 is to be fitted behind the 2nd stage disk. With the fitting of this locking ring, the original 1/4 UNF bolts UB.83877 24-off will be replaced by 24-off UNF studs UB.80548

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Engine stress investigation. Olympus Mk.4 LP compressor 2nd stage dummy weights. Retained ring  PA1716/5/11/2/364  2 December 1953

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Contents:
Ref: 4096SR/4. Drawing of retaining ring for 2nd stage dummy weight

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Olympus Mk.4 LP compressor. Torque tests on 9/16' UNF bolts connecting 1st & 2nd stage discs (Bolts in S.97 material).  PA1716/5/11/2/365  11 December 1953

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Ref: 4096SR/4. List of tabulated checks and tests. Torque recommended 80ft.lb. + 5 using engine oil

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: Interim report on the testing of B.0L.4 & 2nd stage LP conical disc assembly  PA1716/5/11/2/366  21 December 1953

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Ref: 4096SR/4. The B.OL.4 LP compressor rotor contains two coned assemblies, the first incorporating the 1st & 2nd stage discs, and the second, the 4th & 5th stage discs

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed: B.0L.4 LP compressor. Notes on meeting to discuss action to be taken following overspeed tests of first two stages  PA1716/5/11/2/367  1 January 1954

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Ref: 4096R/4. 1 The overspeed tests had disclosed permanent distortion of the rim of the second stage disc which had heeled in a forward direction. The spacer ring flange had also run on the rear face. At design rpm, dilation of the second stage disc was more than twice that of the first stage

Bristol Aeroplane Company Limited. Engine Stress investigation. Olympus overspeed: Olympus Mk.4 LP compressor dummy blade weights  PA1716/5/11/2/368  7 January 1954

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Contents:
Ref: 4096SR/4. Correction of existing weights in order that the CG corresponds to that of the blades. Mods using BACE 76 plugs. Mods using BACE bolts

Bristol Aeroplane Company Limited. Engine Stress investigation. Olympus overspeed: Overspeeding of Olympus Mk.4 LP compressor 1st & 2nd stage coned assembly  PA1716/5/11/2/369  7 January 1954

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Contents:
Ref: 4096SR/4. The combined 1st & 2nd stages were assembled to Schemes SCS1483and RL19824, and subjected to an overspeed test in accordance with the Stress Office instruction 4096SR/4 Issue 2

Bristol Aeroplane Company Limited. Engine Stress investigation Memo. Olympus overspeed: Overspeeding of Olympus Mk.4 LP compressor 1st stage dummy blade weights  PA1716/5/11/2/370  13 January 1954

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4096SR/4. Memo from Stress Office: In view of increased abutment between the 1st stage dummy blade weight root fixing and the redesigned spacer ring of the 1st and 2nd stage LP compressor coned assembly, it is thought that the nine rejected dummy weights mentioned in your report of the 7th January 1954 ref ED/INS/KJ/IM/98. The dummy blade weights in question, should have their retaining tangs on the forward face made true to drawing, and would Mr Newport please make arrangements for this work to be carried out. The full 1st stage set of weights will be modified to our instructions detailed in our note to Mr Edmunds dated 12 January 1954 Ref CE/SWM/KC/3889

Bristol Aeroplane Company Limited. Engine Stress investigation Memo. Olympus overspeed: Overspeeding of Olympus Mk.4 LP compressor dummy blade weights  PA1716/5/11/2/371  19 January 1954

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Ref: 4096/4. Memo from Chief Engineer No.4 shop to Stress office: With reference to your note of the 12th instant, and confirming our conversation yesterday, concerning the modifications which you have requested shall be made to dummy blade weights to Scheme MS.1699, we would confirm that there are some 400 weights involved and that the cost of the modifications to these weights will be approximately £2,000 to £2,500. You may consider this to be somewhat excessive but we would explain that the heavy metal plugs which are required to be fitted to the blades will have to be split up from hexagon bar of fixed size, since this particular metal is only supplied in that form and, in addition, each of the weights requires jig boring or jig drilling for at least two holes. Drawing DT291567-71 attached

Bristol Aeroplane Company Limited. Engine Stress investigation Memo. Olympus overspeed: Overspeeding of Olympus 4 components. 1st & 2nd stage LP coned compressor rotor assembly. Issue 3  PA1716/5/11/2/372  20 January 1954

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Ref: 4096SR/4. The following procedure is to be adopted when overspeeding the Olympus 4 1st & 2nd stage LP coned assembly

Bristol Aeroplane Company Limited. Engine Stress investigation Memo. Olympus overspeed: Overspeeding of Olympus 4 components. 2nd & 1st stage LP coned compressor rotor assembly  PA1716/5/11/2/373  17 February 1954

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Ref: 4096SR/4. Further to our note of the 17th inst ref CE/SWM/KC/4031 regarding the rebuild and testing of the 1st and 2nd stage coned assembly in reverse, the following additional checks would be of invaluable consequence in the redesigning of the coned pair

Bristol Aeroplane Company Limited. Engine Stress investigation Memo. Olympus overspeed: Overspeeding of Olympus 4 components. Retainer ring for the 4th stage LP dummy blade weights  PA1716/5/11/2/374  17 February 1954

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Ref: 4096R/4. It has been decided to carry out overspeeding investigations on the Olympus 4 LP compressor 4th & 5th staged coned assembly

Bristol Aeroplane Company Limited. Engine Stress investigation Memo. Olympus overspeed: Overspeeding of Olympus 4 components. Acceptance tests on the 4th stage LP coned rotor assembly  PA1716/5/11/2/375  18 February 1954

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Ref: 4096R/4. It was decided at a meeting on the 16th February that spinning tests should be carried out on the 4th and 5th stage LP compressor coned assembly in view of the recent findings on the first two stages of this rotor

Bristol Aeroplane Company Limited. Engine Stress investigation Memo. Olympus overspeed: Overspeeding of Olympus Mk.4 Components. 4th & 5th stage LP coned compressor rotor assembly  PA1716/5/11/2/376  18 February 1954

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Ref: 4096SR/4. The following procedure is to be adopted when overspeeding the Olympus Mk.4 4th & 5th stage LP coned assembly: Drawing CE/SWM/KC/4032 attached

Bristol Aeroplane Company Limited. Engine Stress investigation. Olympus overspeed: Experimental Department report 266/54. Olympus Mk.4 LP overspeed compressor rotor. rebuild of 1st & 2nd stage disc assembly (2nd rebuild)  PA1716/5/11/2/377  19 February 1954

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Ref: 4096/4. Following the overspeed test of the above assembly after the initial build, ref EDR.745/54, the unit was rebuilt in accordance with Research Programme Note 2129/B. The following new parts to scheme were incorporated...

Bristol Aeroplane Company Limited. Engine Stress investigation report. Olympus Mk.4 overspeed summary. Coned assembly  PA1716/5/11/2/378  1 January 1954

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Ref: 4096SR/5. Section 1: Olympus 4 coned assembly - 1. 2nd stage dummy weights unsatisfactory. 2 Torque tests carried out on 20 - 7/16 bolts in test blocks resulting in 70lb.ft. 3 Tested to 7000 rpm when a 2nd stage weight moved axially about 1/4'. Test discontinued. 4 Although large elastic displacements were apparent, no permanent distortion was found in the discs. Section 2: Compressor rotor

Bristol Aeroplane Company Limited. Stress investigation. Second interim report on the testing of B.OL.4. 1st 7 2nd stage LP critical disc assembly. CDD T.555/54.  PA1716/5/11/2/379  22 February 1954

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4096SR/4. Issued by Component Development Department. Aero Engine Division Bristol Aeroplane CO. Ltd. In view of previous tests on the B.OL.4 LP compressor 1st & 2nd stage coned assembly, which indicated that the rim of the 2nd stage disc was tipping excessively under centrifugal load, a re-designed spacer ring intended to give more support to the disc rim was incorporated in the 2nd build of the assembly. A series of spinning tests have now been acrried out to obtain dilation and axial displacement characteristics of the assembly under centrifugal loading

Bristol Aeroplane Company Limited. Engineering Department. Engine Stress investigation. Olympus overspeed. Experimental clearance B.OL.4 LP 4th & 5th stage rotor blades for overspeed testing  PA1716/5/11/2/380  22 February 1954

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Ref: 4096/4. Stress Office. In order to test a coned assembly of the 4th & 5th stage rotor discs schedule assembly B.91681 has been prepared listing the existing parts to be obtained from the rotor assembly, also a new part B.91862 Blade weight retainer (4th stage), which is to be manufactured. Test Plant Design Office will make an adaptor to suit these discs

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed. Engine Stress investigation. Overspeeding Olympus 4 component LP compressor rotor  PA1716/5/11/2/381  4 March 1954

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Ref: 4096SR/4. Dr Hooker has ruled at a recent meeting that the Olympus 4 LP compressor rotor shall be designed and tested to try light alloy blades (BACE 301) to replace the existing steel rotor blades in BAC 245

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed. Engine Stress investigation. Third interim report on spinning tests acrried out on the B.OL.4 1st & 2nd stage coned assembly  PA1716/5/11/2/382  10 March 1954

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Ref: 4096SR/4. Report T.561/54. OO.703102. Previous tests on the B.OL.4 LP compressor rotor 1st & 2nd stage coned assembly, have shown the unit to be incapable of withstanding the centrifugal loads imposed on it at proposed engine running speeds without undue distortion. Before revising the design of the assembly, it was considered expedient to obtain as much information as possible from the existing assembly, to supplement the theoretical basis on which design is based

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed. Notes on a meeting to discuss Olympus 4 LP compressor rotor held on 10 march 1954  PA1716/5/11/2/383  11 March 1954

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Ref: 4096SR/4. The Stress office reviewed the design position in the light of the latest decision to introduce aluminium blades in the LP compressor assembly. It has been found that whilst the material change offered some relief, the problem of elastic canting of the rims of the current compressor discs still persisted. The maximum axial movement at the blade tip occurred on the 2nd stage and amounted to approximately 3170 in. After reviewing the blade clearances it was agreed that this movement be tolerated for initial running

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed. Overspeed summary. Olympus 4 LP compressor 1st & 2nd stage coned assembly  PA1716/5/11/2/384  12 March 1954 - 15 March 1954

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Contents:
Ref: 4096SR/4. 1. Includes related Engine Stress Investigation

Bristol Aeroplane Company Limited. Stress Office. Olympus overspeed. Overspeeding Olympus 4 components. 1st & 2nd stage LP coned compressor assembly. Carrying representative A1 alloy blades Issue 1  PA1716/5/11/2/385  17 March 1954

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Ref: 4096SR/4. Attached full report with drawing

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Olympus 4 compressor 1st & 2nd stage LP DBW 6,320rpm  PA1716/5/11/2/386  30 March 1954

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Ref: 4096SR/4. 1st & 2nd stage dummy blade weights to refinement 10%T/C 7% T/C tip A1 alloy blades with no correction applied for rim weights. Previous calculations referred to: 4096/4. Drawing on last page

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Olympus Mk.4 compressor dummy blade weights  PA1716/5/11/2/387  31 March 1954

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Ref: 4096SR/4. Modified dummy blade weights representing 12% T/C root 5% T/C tip (3rd, 4th, 5th stages) 10% T/C root, 7% T/C tip (1st & 2nd stages) A1 alloy blades without correction to rim couples. Scheme of drawing used: MS.1571

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Olympus Mk.4 components. 1st & 2nd stage LP coned compressor assembly. Carrying reprentative A1 alloy blades with no correction for rim slope. issue 1  PA1716/5/11/2/388  31 March 1954

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Ref: 4096SR/4. Enclosed is the overspeed schedule covering the investigations to be carried out by the Olympus 4 1st & 2nd stage coned LP assembly, incorporating the modified 1st stage spacer ring to 03S.273/7. 3-page report including drawing on final page

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Olympus Mk.4 components. Modified LP compressor 3rd, 4th. 5th stage dummy blade weights  PA1716/5/11/2/389  1 April 1954

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Ref: 4096SR/4. Fourth interim report on spinning tests carried out on the B.OL.4 1st & 2nd stage LP coned assembly. Report T.573/54. OO.703102. Previous tests on the B.OL.4 1st & 2nd stage LP compressor coned assembly have shown the assembly to be incapable of withstanding the loads imposed upon it by the employment of steel blades at proposed engine running speeds; the centrifugal loads due to to the blade weights being out of line with the resisting forces in the disc sections, set up a couple at the rims of the discs causing them to tilt to such an extent that permanent distortion occurred at speeds below proposed engine take-off rpm

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Research Build note: B.OL.4 LP 1st & 2nd stage coned assembly  PA1716/5/11/2/390  7 April 1954

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Contents:
Ref: 4096/4. The above assembly is now to be built with dummy blade weights to simulate aluminium blades. Details of the assembly are shown on Scheme 03S273/7

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Overspeeding Olympus 4 components. 4th & 5th stage compressor assembly. Carrying representative A1 alloy blades with no correction for rim slopes  PA1716/5/11/2/391  15 April 1954

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Contents:
Ref: 4096SR/4. Enclosed herewith is the overspeed schedule covering investigations to be carried out on the Olympus 4th 7 5th stage coned LP compressor assembly

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Experimental Department report 602/54. Olympus MK.4 overspeed compressor rotor. Rebuild of 1st & 2nd stage disc, 4th build  PA1716/5/11/2/392  27 April 1954

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Contents:
Ref: 4096SR/4. Following the overspeed test of the above assembly, after the 3rd build, ref EDR.534/4, the unit was stripped and rebuilt inacordance with Research programme 212/D

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/1. B.OL.4 LP 4th & 5th stage coned assembly for overspeed testing  PA1716/5/11/2/393  3 May 1954 - 6 May 1954

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Contents:
Ref: 4096SR/4. The above is now to be built with dummy blade weights DT.527773 and DT.327774 to simulate aluminium blades. Scheme SCS.1641 shows details of the assembly with the exception of the dummy blade weight. Includes related Research Build Note RB.6/2. B.OL.4 LP 1st & 2nd stage coned assembly for overspeed testing: Ref: 4096SR/4. The above wheel is being returned to No.4 Shop following completion of the testing and is to be check balanced and dimensionally checked as laid down in the Stress office Schedule

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Notes on meeting to discuss overspeed test on Olympus 4 compressor 3.5.54  PA1716/5/11/2/394  4 May 1954

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Contents:
Ref: 4096SR/4. 1 First two stages LP compressor. 2 HP compressor - complete assembly.

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Olympus Mk.4 LP compressor 1st & 2nd stage dummy weights 6,600 rpm  PA1716/5/11/2/395  13 May 1954

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Contents:
Ref: 4096SR/4. 1st & 2nd stage dummy blade weights to represent 10% root, 2% T/C tip titanium blades for curved discs (see MS1783). Scheme or drawings used MS1783, BT111101 & 3. Previous calculations referred to: 4096SR.4 30 April 1954; 4356/2 4 May 1954

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Olympus Mk.4 LP compressor 1st & 2nd stage dummy weights 6,600 rpm  PA1716/5/11/2/396  14 May 1954

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Contents:
Ref: 4096SR/4. 1st & 2nd stage dummy blade weights to represent 10% T/C root, 2% T/C tip AL.Alloy (BACE 301) blades for redesigned discs to MS1756. Scheme or drawings used: MS1756. Previous calculations referred to: 4096/4 13 May 1954

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/3. B.OL.4 LP 4th & 5th stage coned assembly for overspeed testing  PA1716/5/11/2/397  19 May 1954

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Contents:
Ref: 4096SR/4. Further to note RB.6/1 difficulty in tightening the nuts on the hub bolts has been experienced due to the small diameter spot face on the adaptor; to overcome this, special stepped nuts are now to be fitted, therefore the UB.80554 special nuts 10-off, are replaced by BS.26023 Special Nuts 10-off supplied by TPDO. Scheme SCS.1641/2 has been prepared to show this change

Bristol Aeroplane Company Limited. Memo from Stress Office. Engine stress investigation. Olympus overspeed. Overspeeding Olympus 4 components LP compressor rotor assembly. Research investigations. Issue.  PA1716/5/11/2/398  20 May 1954

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Contents:
Ref: 4096SR/4. Enclosed herewith is the overspeed schedule covering investigations to be carried out on the complete LP compressor rotor assembly comprising Olympus 4 components. Includes related Fifth Interim report on spinning test carried out on the B.OL.4 1st & 2nd stage LP coned assembly: Ref: 4096SR/4. Although previous rig test have shown the B.OL.4 LP compressor rotor 1st & 2nd stage coned assembly to be incapable, at the proposed engine speeds, of withstanding the loads imposed by the steel blades for which it was originally designed, it was visualised that the substitution of aluminium alloy rotor blades might permit the use of the existing rotor design

Bristol Aeroplane Company Limited. Memo from Stress Office. Engine stress investigation. Olympus overspeed. Overspeeding Olympus 4 components LP compressor rotor assembly Research Investigations Issue 1  PA1716/5/11/2/399  20 May 1954

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Contents:
Ref: 4096SR/4. Dimensional check before assembly: A complete check should be taken of all major dimensions, together with the degree of coning on the forward faces, of the 1st & 4th and aft faces of the 2nd & 5th stage discs. Report T.603/54. OO.703130

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/4. BOL.4 LP 4th & 5th stage coned assembly for overspeed testing  PA1716/5/11/2/400  9 July 1954

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Contents:
Ref: 4096/4. The above assembly has been returned to No.4 Shop after completing its tests and is to be balanced and dimensionally checked, as laid down in the Stress Office Schedule, after which it is to be completely stripped and inspected

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Stripping & tests on B.OL.4 LP assembly compressor rotor 1st & 2nd stage coned assembly  PA1716/5/11/2/401  14 July 1954

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Contents:
Ref: 4096SR/4. Total running time 22.5 hours. Issued by Component development Department, Aero Engine Division, Bristol Aeroplane Co. Ltd. Report T.630/54. OO.703130. Fifth Build Al blades

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Overspeed tests on B.OL.4 LP compressor rotor 4th & 5th stage coned assembly  PA1716/5/11/2/402  21 July 1954

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Contents:
Ref: 4096/4. Running time 5.5 hours. Report T.635/54

Bristol Aeroplane Company Limited. Experimental Department to Stress Office. Engine stress investigation. Olympus overspeed. Overspeed tests on Olympus Mk.4 compressor 4th & 5th stage rotor discs B.79986 & B.79987  PA1716/5/11/2/403  22 July 1954

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Contents:
Ref: 4096/4. The above new discs were subjected to overspeed dilation and checks to Schedule 4096SR/4 Issue. Upon satisfactory completion of tests, subsequent examination and dimensional checks revealed no appreciable radial or axial changes and all components were in a satsifactory condition. Summary of tests is attached in tabulated format

Bristol Aeroplane Company Limited. Experimental Department to Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/5. BOL.4 LP compressor rotor for overspeed tests  PA1716/5/11/2/404  13 August 1954

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Contents:
Ref: 4096SR/4. Following individual testing of stages 1 & 2, and stages 4 & 5, the complete rotor unit is now to be built with dummy blade weights to simulate aluminium blades, reference scheme SCS.1641/2, 03S.273/3 and 03S.273/7

Bristol Aeroplane Company Limited. Experimental Department to Stress Office. Engine stress investigation. Olympus overspeed. Acceptance overspeed tests on Olympus 6D compressor assembly. Issue 2.  PA1716/5/11/2/405  24 August 1954

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Contents:
Ref: 4096SR/4. It should only be necessary to overspeed the first three of these rotors

Bristol Aeroplane Company Limited. Experimental Department to Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/6. B.OL.4 compressor rotor for overspeed tests  PA1716/5/11/2/406  27 August 1954

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Contents:
Ref; 4096SR/4. Further to RB.6/5 the following modification is to be incorporated to enable the assembly to be built

Bristol Aeroplane Company Limited. Experimental Department to Stress Office. Engine stress investigation. Olympus overspeed. Turbine Programme Note TP.1801/11. B.OL.6D Build 601 (First Build). Initial build for acceptance test  PA1716/5/11/2/407  7 September 1954

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Contents:
Ref: 4096/4. Further to TP.1801/10, the following modifications are to be incorporated into the initial build of this engine

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/7. B.OL.4 LP compressor rotor for overspeed tests  PA1716/5/11/2/408  23 September 1954

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Contents:
Ref:4096/4. Further to RB.6/5, it has now been decided to bring the above rotor in line with main engine by fitting the latest type dowels and studs at the spacer ring and rotor discs, stages 3-5, stages 1 & 2 rotor discs are already in line

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Olympus 6/1 & 6/2 LP compressor 6,600 rpm stage 4. MS.2269 representing rotor blades (stiffness) for steel discs. Blade drawing B.121044  PA1716/5/11/2/409  c. October 1954

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Contents:
Ref: 4096/4. Attached: LP compressor 6,600 rpm 5th stage. Blade drawing B.118255

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/8. B.OL.4 compressor rotor for overspeed tests  PA1716/5/11/2/410  15 October 1954

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Contents:
Ref: 4096/4. Further to RB.6/7, please note B.79986 rotor disc stage 4, which was modified to drawing B89222, is now to be repart numbered B.101474ND, due to the 10-off holes being 37/64 dia. instead of .5625 dia.

Bristol Aeroplane Company Limited. Experimental Department to Stress Office. Engine stress investigation. Olympus overspeed. Olympus MK.6D2 & 6/1 LP compressor dummy blade weights  PA1716/5/11/2/411  26 October 1954 - 27 October 1954

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Contents:
Ref: 4096SR/4. Dummy blade weights representaing AL. Alloy rotor blades with Mk.101 blade root fixings for 1st, 2nd, 3rd, 4th & 5th staged at 6,600 rpm. Schemes or drawings used: B.102381-5 blades; B.102386-90 discs. Previous calculations referred to: 4364/2 20 August 1954

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Component Department: Overspeed test results B.OL.4 LP compressor rotor with dummy blade weights  PA1716/5/11/2/412  31 October 1954

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Contents:
Ref: 4096/4

Bristol Aeroplane Company Limited internal memo Stress Office. Engine stress investigation. Olympus overspeed. Olympus No.603 - HP compressor rotor overspeed  PA1716/5/11/2/413  10 November 1954

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Contents:
Ref: 4096/4. It has been agreed by the Stress Department that the overspeed test on Olympus No.603 HP compressor rotor can be waived since an overspeed will be required on Olympus no.604's rotor with Titanium discs

Bristol Aeroplane Company Limited. Report to Stress Office. Engine stress investigation. Olympus overspeed. Turbine Programme Note: Tp.1955/3. Olympus Mk.6D. Engine No.603 (first Build ). Initail build for acceptance test  PA1716/5/11/2/414  11 November 1954

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Contents:
Ref: 4096/4. With reference to TP.1955 which instructed the build of the HP compressor rotor for overspeed testing, it has now been agreed with Stress Department that overspeed test on this rotor need not be carried out and the Instruction on TP.1955 is therefore cancelled. MoS technical agreement CE/RCP/PJEH/18335

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Research Build Note RB.6/10. B.OL.6 LP compressor rotor for overspeed tests  PA1716/5/11/2/415  11 November 1954

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Contents:
Ref:4096/4. Followin inspection, the above units is to be rebuilt to the following standards, which will change the title from B.OL.4 to B.OL.6

Experimental Department Report No.661/59: Olympus Mk.101, Engine OL.501  PA1716/5/11/2/416  4 May 1959

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Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Component Development Department Report T.711/54. Spinning test on B.OL.4 LP compressor  PA1716/5/11/2/417  25 November 1954

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Contents:
Ref: 4096/4. Total running time 10 hours. MoS contract SP/6/Eng/7274

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Turbine Programme Notes TP.1956/5. OLympus Mk.6D Engine No.601 (First build). Initial build for acceptance test  PA1716/5/11/2/418  10 December 1954

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Contents:
Ref: 4096/4.Further to TP.1956/4, the following additional modifications are required during the initial build of this engine

Bristol Aeroplane Company Limited internal memo Stress Office. Engine stress investigation. Olympus overspeed. Acceptance overspeed test Olympus 6D on components. Oil separator  PA1716/5/11/2/419  16 December 1954

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Contents:
Ref: 4096/4. Three Olympus 6D oil separators have been successfully overspeeded to cover maximum engine take-off conditions at 6320 rpm. This process could now be deleted from the manufacturing process for these de-rsted engines

Bristol Aeroplane Company Limited internal memo Stress Office. Engine stress investigation. Olympus overspeed. Turbine Programme Note TP.2057/2. OLympus Mk.6-1. Engine No.602 (4th Build) Rebuild for development testing  PA1716/5/11/2/420  16 December 1954

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Contents:
Ref: 4096/4. On completion of crack testing of the LP compressor rotor discs, the LP compressor is to be built with dummy blade weights and despatched to the Research Department overspeed rig, Gypsy Patch, where overspeeding 10% over 6600 rpm is to be carried out to Stress Department instructions. On completion, the LP rotor is to be built for fitting to the engine as already instructed

Bristol Aeroplane Company Limited. Stress Office. Engine stress investigation. Olympus overspeed. Acceptance overspeed tests on Olympus 6D components. LP compressor assembly. Issue 3  PA1716/5/11/2/421  16 December 1954

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Contents:
Ref;4096SR/4. The balanced Olympus 6D compressor assembly, complete with dummy blade weights to DT.327709-10 and DT.327772-4 in the first to 5th stage respectively, in the following manner...

Bristol Aeroplane Company Limited internal memo Stress Office. Engine stress investigation. Olympus overspeed. Acceptance overspeed tests on Olympus 6D components. LP compressor assembly. Issue 3  PA1716/5/11/2/422  16 December 1954

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Contents:
Ref: 4096SR/4. In view of the satisfactory overspeed experienced on the first Olympus 6D LP compressor rotor assembly, carrying representative A1 Alloy rotor blades, it has been ruled by Dr Hocker, that a similar rotor be further overspeed tested to 7260 rpm, to cover Olympus 6 take-off conditions of 6600 rpm. It has been agreed that on the next strip of Olympus 6 engine, the LP rotor will be built for overspeed and the test carried out in accordance with Stress Department Schedule Issue

Bristol Aeroplane Company Limited internal memo Stress Office. Engine stress investigation. Olympus overspeed. Acceptance overspeed tests on Olympus 6D components. LP compressor assembly with 101 type root fixings  PA1716/5/11/2/423  22 December 1954

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Contents:
Ref: 4096SR/4. Enclosed, herewith, is the Stress Department overspeed schedule covering acceptances test on the Olympus 6D lp compressor rotor, carrying representative A1 Alloy dummy blade weights with Olympus 101 type root fixings in stages 3, 4 and 5. Dilation checks should be carried out over the last three stages on the first rotor only

Bristol Aeroplane Company Limited internal memo Stress Office. Engine stress investigation. General design information: Olympus III LP compressor blade design  PA1716/5/11/2/424  12 April 1951 - 3 July 1951

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Contents:
Section D. Issued by Performance & Aerodynamic department PIM.42. The compressor design is based on the following design point of assumption at ICAM. SLS conditions: Page A1: Air mass flow 212 lbs/sec. Compressor rpm 6,200. Compressor total pressure ratio 2.38. Page A2: Olympus III data LP compressor 6,200 rpm 212 lbs/sec ICAN sea level static (tables). Page A3: Olympus III LP compressor rotor blade data. Page A4: Olympus III LP compressor stator blade data. Page A5: Graph of Olympus III LP compressor rotor blades. Page A6: Graph of Olympus LP compressor stator blades. Includes related addendum

Bristol Aeroplane Company Limited internal memo Stress Office. Performance & Aerodynamics Department. General design information: Olympus 3HP compressor blade design  PA1716/5/11/2/425  19 April 1951

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Contents:
Section D. PDM.41. The compressor design is based upon the following assumptions at ICAN. SLS conditions. Air mass flow 212 lbs/sec. Compressor rpm 7,800. Compressor total pressure ratio 4.0. Report also contains HP compressor tables: 7,800 rpm data at sea level. Stator blade data. Graph for HP inlet guide vanes; Graph HP compressor blades

Bristol Aeroplane Company Limited internal memo Stress Office. Performance & Aerodynamics Department. General design information: Olympus III turbine design  PA1716/5/11/2/426  1 March 1951

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Contents:
Section D.GN.399. DCE/NRO/847B/P. Drawing MS.1394: Temperature and pressure in turbine at ICAN sea level static maximum rpm entry. Total temp 1020CK. Drawing GR 2770: Inertia bending moment diagram. (REJ 2 January 1952). Drawing GR 2769: Inertia shear force diagram. (RJ 2 January 1952). Drawing GR.2773: Pressure thrust diagram. (REJ 4 January 1952). Drawing GR.2774: Torque reaction diagram. (RJ 8 January 1952). Drawing GR.2772: Gyroscopic bending moment diagram.(RJ 4 January 1952). Drawing GR.2771: Gyroscopic shear force. [RJ]. Graph GR.2803/A: Dead load shear force moment for Olympus III LP system. (KLB 21 January 1952). Sheet LP.1. Graph GR.2803/C: Dead load force & bending moment for Olympus III HP system. (KLB 21 January 1952). Sheet HP 1. Graph GR.2803/B: Gyroscopic shear force & bending moment for Olympus III LP system.(KLB 21 January 1952). Sheet LP 2. Graph GR.2803/D: Gyroscopic shear force & bending moment for Olympus III HP system.(KLB 21 January 1952). Sheet HP 2.

Bristol Aeroplane Company Limited internal memo Stress Office. Performance & Aerodynamics Department. General design information: Olympus III LP compressor rotor blades  PA1716/5/11/2/427  April 1952

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Contents:
4263/7. Section D. Graph GR2798: Olympus III LP compressor 1st stage disc and stresses. Graph GR2799: Olympus III LP compressor 2nd stage disc and stresses. Graph GR2800: Olympus III LP compressor 3rd stage disc and stresses. Graph GR2801: Olympus III LP compressor 4th stage disc and stresses. Graph GR2802: Olympus III LP compressor 5th stage disc and stresses. Page B7 to B12: Olympus III LP compressor rotor spacing rings. tables and drawings. Page B13: Compressor and turbine rotating parts. Polar moment of inertia. Page C2. Graph GR2812: Olympus III HP compressor 1st stage disc and stresses. Page C3. Graph GR2813: Olympus III HP compressor 2nd satge disc and stresses. Page C4. Graph GR2814: Olympus III HP compressor 3rd stage disc and stresses. Page C5. Graph 2815: Olympus III HP compressor 4th stage disc and stresses. Page C6. Graph 2816: Olympus III HP compressor 5th stage disc and streses. Page C7. Graph 2817: Olympus III HP compressor 6th stage disc and stresses. Page C8. Graph 2818: Olympus III HP compressor 7th stage disc and stresses.

Bristol Aeroplane Company Limited internal memo Stress Office. Performance & Aerodynamics Department. General design information: Olympus III HP compressor rotor (Graph1)  PA1716/5/11/2/428  [n.d.]

Contents:
Section C. Now part of 1716/5/11/2/427

Bristol Aeroplane Company Limited internal memo. Stress Office Ref4346SR/1: Stress clearance record. Olympus MK.4 HP compressor rotor  PA1716/5/11/2/429  16 September 1953

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Contents:
Section C. Basic scheme 03S 127/8. This note gives general stress clearance to the HP compressor rotor assembly as shown in the above scheme, with the exception of the blading which is the subject of a further note

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4364SR/5: Stress clearance record. Olympus III HP compressor rotor blades  PA1716/5/11/2/430  1953

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Contents:
Section C. Two pages of tables

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4344SR/10: Stress summary. Olympus III HP compressor rotor. Spacing rings  PA1716/5/11/2/431  1953

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Contents:
Section C. Scheme 3S.127 Material S.106. ICAN SL Static

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4344SR/10: Stress summary. Olympus III HP compressor rotor. Radial growth & blade tip clearance  PA1716/5/11/2/432  1953

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Contents:
SectionC. Component radial extensions at ICAN SL Static condition (relative to 20 degC)

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4344SR/11: Stress summary. Olympus III HP compressor shafts  PA1716/5/11/2/433  1953

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Contents:
Section C. Scheme 03S.127. Material S.106

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4344SR/10: Stress summary. Olympus III HP compressor rotor. Spacing ring attachment bolts  PA1716/5/11/2/434  1952

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Contents:
Scheme 03S.127. Material S.80

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4173SR/Secret: Olympus Mk.3 HP compressor rotor and turbine rotating parts. Polar moment of inertia  PA1716/5/11/2/435  23 April 1952

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Contents:
OIMI 48/2

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4324SR/16: Stress summary. Olympus III casings. Air intake casing  PA1716/5/11/2/436  1952

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Contents:
Section D. Scheme 03S.114

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4324SR/15. Olympus III LP compressor casings  PA1716/5/11/2/437  1952

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Contents:
Section D. Scheme O3S.136

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4324SR/17. Olympus III LP compressor casings. Intermediate casing  PA1716/5/11/2/438  1952

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Contents:
Section D. Scheme O3S.137

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4324SR/13. Olympus III HP compressor casings  PA1716/5/11/2/439  1952

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Contents:
Scetion D. Scheme O3S.115

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4324SR/14. Stress summary. Olympus III HP delivery casings  PA1716/5/11/2/440  1952

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Contents:
Section D. Scheme O3S.200

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4324SR/15. Stress summary. Olympus III Bolted joints between compressor casings  PA1716/5/11/2/441  1952

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Contents:
Section D

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4314SR/6 & 4314SR/9. Stress summary. Olympus III LP compressor stator blades  PA1716/5/11/2/442  1952

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Contents:
Section D. Scheme O3S.138-141. With drawings

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4314SR/6. Stress summary. Olympus III HP compressor stator blades  PA1716/5/11/2/443  1952

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Contents:
Section D. Scheme O3S.103-108. With tables and drawings

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4344SR/10. Stress summary. Olympus III HP compressor rotor. Coned discs and flying bolts  PA1716/5/11/2/444  1952

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Contents:
Section D. Scheme O3S.127. 1 stand 2nd stage discs

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10. Stress summary. Olympus Mk.3 turbine. HP & LP rotor blade loadings  PA1716/5/11/2/445  25 October 1951

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Contents:
Section E. Graph 2422 Olympus Mk.3 turbine HP & LP rotor blade loadings: 1st stage 101 blades; 2nd stage 79 blades

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10. Summary of blade stresses. Olympus III HP maximum power conditions  PA1716/5/11/2/446  1951

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Contents:
Section E. Blade to PDM.38. Tables. Graphs (2) GR2860 Olympus III HP turbine rotor blade stresses (4454SR/10); Nimonic 80A. PDM38. Graph GR2716 Olympus III turbine HP rotor blade stresses.(4454SR/10)

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10. Summary of blade stresses. Olympus III LP summary of blade stresses at maximum power  PA1716/5/11/2/447  1951

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Contents:
Section E. Blade to PDM.38. Page E.7 Blades at maximum cruise. Page E.8 Summary of blade data. Sheet 1: Graph GR2896 Olympus III turbine. Redesigned LP rotor blades stresses (4454SR/10). Sheet 2: Graph GR2896 Olympus III turbine. Redesigned LP rotor blade stresses

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10 & 4434SR/13. Summary of blade root stresses and data. Olympus Mk.3 HP stage  PA1716/5/11/2/448  1951

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Contents:
Section E

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10 & 4434SR/13. Summary of blade root stresses and data. Olympus Mk.3 LP stage  PA1716/5/11/2/449  1951

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Contents:
Section E

Bristol Aeroplane Company Limited internal memo. Stress Office  PA1716/5/11/2/450  1951 - 1952

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10. Graph 2719A Olympus Mk.3 HP Turbine wheel. Total radial and hoop stresses 7800 rpm  PA1716/5/11/2/450/1  26 September 1951

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Contents:
Graph 2719A: Olympus Mk.3 HP turbine wheel and hoop streses at7800 rpm

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10. Graph 2719B Olympus Mk.3 HP Turbine wheel. Total radial and hoop stresses 7800 rpm  PA1716/5/11/2/450/2  26 September 1951

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Contents:
Section E

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10 & 4434SR/16. Olympus Mk.3 Turbine wheel data. LP stage  PA1716/5/11/2/450/3  1951

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Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4444SR/10. Graph GR2717A Olympus Mk.3 LP Turbine wheel. Total radial & hoop stresses at 6200 rpm  PA1716/5/11/2/450/4  12 September 1951

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Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4444SR/10. Graph GR2717B Olympus Mk.3 LP Turbine wheel. Total radial & hoop stresses at 6200 rpm  PA1716/5/11/2/450/5  12 September 1951

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Contents:
Section E

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4434SR/16 & 4444SR/10. Olympus Mk.3 LP Turbine. Gyroscopic deflections of turbine rotors (SchO3S.157)  PA1716/5/11/2/450/6  14 February 1952

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Contents:
Section E. HP gyroscopic deflections for case 4 (flat spin)

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4434SR/15. Olympus Mk.3 turbine. Interstage rotating diaphragm  PA1716/5/11/2/450/7  21 January 1952

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Contents:
Section E

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4434SR/15. Olympus III turbine. Interstage rotating diaphragm  PA1716/5/11/2/450/8  15 January 1952

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Contents:
Section E. Graph GR2794 Olympus III turbine interstage rotating diaphragm at 7800 rpm

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4434SR/16. Olympus Mk.3 HP turbine shaft. ICAN SL static conditions 27,500HP at 7800 rpm  PA1716/5/11/2/450/9  1951

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Contents:
Section E. With drawing and tables

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4434SR/16. Olympus Mk.3 LP turbine shaft. Summary of stresses in shaft (tons per sq.in.)  PA1716/5/11/2/450/10  8 November 1951

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Contents:
Section E

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4454SR/10 & 4434SR/16. Turbine wheel data. Olympus Mk.3 HP stage  PA1716/5/11/2/450/11  1951

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Contents:
Section E

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4424SR/14. Olympus Mk.3 LP turbine casing. Summary of stresses in casing and bolt joints  PA1716/5/11/2/451  6 February 1952

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Contents:
Section F. 2 page report with drawings and tables

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 48SR/6. Olympus Mk.3  PA1716/5/11/2/452  1952

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 48SR/6. Olympus Mk.3 turbine Annular combustion chamber. Summary of stresses  PA1716/5/11/2/452/1  13 March 1952

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Contents:
Section F. O3S.151

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 48SR/6. Olympus Mk.3 Cannular combution chamber. Summary of stresses  PA1716/5/11/2/452/2  26 March 1952

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Contents:
Section F. O3S.191. Outline drawing of combustion chamber

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4414SR/7. Olympus Mk.3 turbine. HP & LP stator blade loadings. 1stGraph GR2421 stage 133 blades; 2nd stage 89 blades  PA1716/5/11/2/453  24 October 1951

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Contents:
Section F

Bristol Aeroplane Company Limited internal memo. Stress Office. Olympus Mk.3  PA1716/5/11/2/454  1952

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4414SR/7. Olympus Mk.3 turbine LP stator. General blade data  PA1716/5/11/2/454/1  1 February 1952

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Contents:
Section F

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4424SR/15. Olympus Mk.3 turbine casing. No.8 bearing diaphragm  PA1716/5/11/2/454/2  14 February 1952

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Contents:
Section F. O3S.157

Bristol Aeroplane Company Limited internal memo. Stress Office Ref6894SR/8. Olympus Mk.3 turbine. Changes in clearance between stators and rotors  PA1716/5/11/2/454/3  11 March 1952

Contents:
Section F. Drawings MS1410 and figures by KLB

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4414SR/7. Olympus Mk.3 turbine HP stator  PA1716/5/11/2/454/4  22 January 1952

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Bristol Aeroplane Company Limited internal memo. Stress Office Olympus Mk.3 turbine. Main C/L bearings MS.1240. Operating conditions  PA1716/5/11/2/455  1951

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Contents:
Section G

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4434SR/16. Stresses in Olympus Mk.3 LP compressor-turbine thrust coupling under catapulting conditions (Case 5)  PA1716/5/11/2/456  January 1952

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Contents:
Section H: Gear drives and couplings

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5214SR/12. Stress summary for starter drive Scheme 03S.124 & 3S.143. Olympus Mk.3  PA1716/5/11/2/457  22 January 1952

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Contents:
Section H: Gear drives and couplings

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5214SR/12. Stress summary for hydraulic drive Scheme 03S.124 & 03S.143. Olympus Mk.3  PA1716/5/11/2/458  22 January 1952

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Contents:
Section H: Gear drives and couplings

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5214SR/11. Stress summary for pump, oil pump & Tachometer drives. Scheme 03S.159. Olympus Mk.3  PA1716/5/11/2/459  21 January 1952

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Contents:
Section H: Gear drives and couplings. Conditions (take-off) Fuel flow 1100 gall/hr. Fuel pump 23 hp (Lucas); Pressure rise 1500 lbs/sqr in. tachometer 1 hp. Pressure & scavenge pump 1 hp

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5214SR/13. Stress summary for Tachometer drives. Scheme 03S.153. Olympus Mk.3  PA1716/5/11/2/460  11 January 1952

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Contents:
Section H: Gear drives and couplings

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5214SR/13. Stress summary for accessory gear box (Internal unit). Scheme 03S.152. Olympus Mk.3  PA1716/5/11/2/461  11 January 1952

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Contents:
Section H: Gear drives and couplings

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5214SR/13. Stress summary for Auxiliary scavenge pump. Scheme 03S.130. Olympus Mk.3  PA1716/5/11/2/462  26 September 1951

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Contents:
Section H: Gear drives and couplings

Bristol Aeroplane Company Limited. Provisionalbalancing for Olympus Mk.3 HP compressors  PA1716/5/11/2/463  1951 - 1952

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/5. Provisional balancing diagram for Olympus Mk.3Oil tube unit  PA1716/5/11/2/463/1  10 January 1952

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Contents:
Section J: Balancing. Drawing MS.1315. 1 of 2

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/5. Provisional balancing diagram for Olympus Mk.3 HP compressors  PA1716/5/11/2/463/2  10 January 1952

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Contents:
Section J: Balancing. Drawings MS.1315. 2 of 2

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/5. Provisional balancing procedure for Olympus Mk.3 HP compressors  PA1716/5/11/2/463/3  30 August 1951

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Contents:
Section J: Balancing. Attached hereto sheet 1 of 2 MS .1315

Bristol Aeroplane Company Limited. Stress Office Ref 5123SR/7. Balancing for Olympus Mk.3 LP compressor  PA1716/5/11/2/464/  1951 - 1952

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/7. Balancing diagram (MS.1325 sheet 1) for Olympus Mk.3 LP compressor  PA1716/5/11/2/464/1  10 January 1952

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Contents:
Section J: Balancing. Drawings MS.1325 Sheet 1 of 2

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/7. Balancing diagram (MS.1325 sheet 2) for Olympus Mk.3 LP compressor  PA1716/5/11/2/464/2  10 January 1952

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Contents:
Section J: Balancing. Drawings MS.1325 Sheet 2 of 2

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/7. Provisional balancing procedure for Olympus Mk.3 LP compressor assembly  PA1716/5/11/2/464/3  17 September 1951

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Contents:
Section J: Balancing. Attached herewith drawings MS.1325 (2 sheets) showing the proposed balancing procedure for the above compressor

Bristol Aeroplane Company Limited. Stress Office Ref 5123SR/6. Balancing for Olympus Mk.3 Turbine  PA1716/5/11/2/465  1951 - 1952

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/6. Balancing diagram (MS.1320 sheet 1) for Olympus Mk.3 HP Turbine to compressor assemblies  PA1716/5/11/2/465/1  10 January 1952

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Contents:
Section J: Balancing. Drawing MS.1320 Sheet 1 of 2

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/6. Balancing diagram (MS.1320 sheet 2) for Olympus Mk.3 LP Turbine to compressor assembly  PA1716/5/11/2/465/2  10 January 1952

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Contents:
Section J: Balancing. Drawing MS.1320 Sheet 2 of 2

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/6. Provisional balancing procedure for Olympus Mk.3 Turbine assemblies  PA1716/5/11/2/465/3  7 September 1951

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Contents:
Section J: Balancing. Attached hereto MS.1320 (2 sheets)

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 5123SR/6 & 5123SR/10. Balancing procedure for Olympus III & Mk.1/2C Turbine assemblies  PA1716/5/11/2/466  20 December 1951

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Contents:
Section J: Balancing. Olympus III: The labyrinth sleeve has been extended from the final dynamic balance (Fig 5 MS.1320 sheet 1). Olympus Mk.1/2C The thrust housing and locating bolts have been excluded from the final dynamic balance (Fig 4 MS.1338, not in our possession) for the same reason as was the labyrinth sleeve in the Olympus III

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4094SR/11. Acceptance overspeed tests on Olympus Mk.3 components. LP compressor assembly  PA1716/5/11/2/467  15 October 1951

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Contents:
Section K: Overspeed testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4094SR/9. Overspeed tests on Olympus Mk.3 components. 1st & 2nd stage HP coned compressor rotor assembly fitted with dummy blade weights  PA1716/5/11/2/468  28 August 1951

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Section K: Overspeed testing. Attached drawing of the above

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4094SR/9. Overspeed tests on Olympus Mk.3 components. 1st & 2nd stage LP coned compressor rotor assembly fitted with dummy blade weights  PA1716/5/11/2/469  15 October 1951

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Section K: Overspeed testing. Attached drawing of the above

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4094SR/9. Acceptance overspeed tests on Olympus Mk.3 components. HP compressor assembly  PA1716/5/11/2/470  15 October 1951

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Section K: Overspeed testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4094SR/10. Acceptance overspeed tests on Olympus Mk.3 components. 1st stage H.46 turbine wheel fitted with dummy weights & interstage diaphgram  PA1716/5/11/2/471  2 October 1951

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Section K: Overspeed testing. Drawing 4096SR/10 attached

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4094SR/10. Acceptance overspeed tests on Olympus Mk.3 components. 1st stage H.46 turbine wheel fitted with skewed dummy weights  PA1716/5/11/2/472  2 October 1951

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Section K: Overspeed testing. Drawing 4096SR/10 attached

Bristol Aeroplane Company Limited internal memo. Stress Office. Pressure test figures for Olympus Mk.3 casings  PA1716/5/11/2/473  21 March 1952

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Section L: Pressure testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 53SR/7. Pressure test drawing MS.1597 for Olympus Mk.4 2nd stage turbine casings  PA1716/5/11/2/474  3 March 1954

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Section L: Pressure testing

Bristol Aeroplane Company Limited internal memo. Stress Office Pressure test drawing MS.1596 for Olympus Mk.4 stator support cone  PA1716/5/11/2/475  3 March 1954

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Contents:
Section L: Pressure testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref Pressure test drawing MS.1639 for Olympus Mk.4 nose bullet  PA1716/5/11/2/476  3 March 1954

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Section L: Pressure testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref Pressure test drawing MS.1639 for Olympus Mk.4 HP compressor casing  PA1716/5/11/2/477  3 March 1954

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Section L: Pressure testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref Pressure test drawing MS.1592 for Olympus Mk.4 air intake casing  PA1716/5/11/2/478  3 March 1954

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Section L: Pressure testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref Pressure test drawing MS.1593 for Olympus Mk.4 intermediate casing  PA1716/5/11/2/479  3 March 1954

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Section L: Pressure testing

Bristol Aeroplane Company Limited internal memo. Stress Office Ref 4171SR/secret. Olympus Mk.4 weight estimate  PA1716/5/11/2/480  February 1952

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OLE.201

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark: Re Modified fuel pump & tachometer generator drives (inner end) for Olympus 6/1 & 6/2  PA1716/5/11/2/481  16 February 1955

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Ref: 5216SR/18 attached: F.1021 Schedule of bearing loads for auxiliary drives (Olympus 6) dated 15 September 1954

Bristol Aeroplane Company Limited. Stress Department. Letter to Ransome & Marles Bearing Co Ltd Newark: Re. Olympus 551 starter, sundstrend & fuel pump drives (outer end)  PA1716/5/11/2/482  18 October 1957

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Ref: 5216SR/16. We enclose herewith a copy of our scheme MS.2736 which shows the majority of the bearings in the above drives and gives their operating conditions. The remainder of the drives have yet to be finalised and will be forwarded at a later date

Bristol Aeroplane Company Limited. Stress Department. Letter to Ransome & Marles Bearing Co Ltd Newark: Re Olympus 551 starter, accessory drives (inner end)  PA1716/5/11/2/483  27 August 1957

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Ref: 5216SR/16. We enclose herwith a copy of scheme MS.2701 which will illustrate the bearings in the above drives and give their operating conditions

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark: Re. Olympus 551 starter, accessory drives (inner ends)  PA1716/5/11/2/484  20 September 1957

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Ref: 5216SR/16. We acknowledge receipt of your letter of the 27th ultimo also a copy of drawing MS.2701 illustrating the bearings you propose in the above drives. We are enclosing herewith a copy of our chart F.1068 outlining all particulars of the bearings in question

Bristol Aeroplane Company Limited. Stress Department. Letter to Ransome & Marles Bearing Co Ltd Newark: Re. Olympus 551 starter, accessory drives (inner ends)  PA1716/5/11/2/485  26 September 1957

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Ref: 5216SR/16. We wish to thank you for your letter and enclose data sheets of the 20th instant M.35 originally shown

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark: Re Olympus 551  PA1716/5/11/2/486  1957 - 1958

Bristol Aeroplane Company Limited. Stress Department. Letter and Drawing F1068.A Letter from Ransome & Marles Bearing Co Ltd Newark: Re Olympus 551 starter, and fuel pump drives (outer end). Schedule of bearings and accessory drives  PA1716/5/11/2/486/1  12 November 1957

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Ref: 5216SR/12. Ransome & Marles Our ref Tech/LEH/KP. Your ref CE/SWM/KC/9347 Stress Department. Drawing F.1068A Schedule of bearings for Olympus Accessory Drives

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark: Re. Olympus 551 Sunstand and hydraulic pump drives. Schedule of bearings for Olympus accessory drives  PA1716/5/11/2/486/2  15 November 1957

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Ref:5216SR/16. Our ref Tech/LEH/KP. Your ref CE/SMM/KC/9387. A copy of our drawing F.1068.B. Issue 2 is attached and F.1068.B, Issue 1, is enclosed giving details of the loading and factors etc.

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark: Re Olympus 551 Sunstand and hydraulic pump drives. Schedule of bearings for Olympus accessory drives drawing F.1068.B  PA1716/5/11/2/486/3  14 November 1957

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Ref: 5216SR/16. Copy of our drawing

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark: Re Olympus 551 Sunstand and hydraulic pump drives. Schedule of bearings for Olympus accessory drives drawing F.1068.B  PA1716/5/11/2/486/4  14 November 1958

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Ref: 5126SR/16. Drawing F.1068.B Issue 1, 2

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark: Re Olympus 551 starter, and fuel pump drives (outer end)  PA1716/5/11/2/486/5  12 November 1957

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Ref:5216SR/16. Bearings K and Y have now been changed to IRJ.10 type outer, cage and rollers. Attached drawing F.1068.A, Issue 2, giving particulars of the various bearing positions with loading capacity and other relevant information

Bristol Aeroplane Company Limited. Stress Department. Re. Olympus 551 accessory drives  PA1716/5/11/2/487  1958

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 551 accessory drives  PA1716/5/11/2/487/1  4 February 1958

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Ref: 5216SR/16. Schedule of bearings for Olympus accessory drives F.1068C

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 551 accessory drives  PA1716/5/11/2/487/2  7 February 1958

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Ref:5216SR/16. Our Ref Tech/LEH/KP. Your ref CE/SWM/KC/9635. The amended loadings etc. as included in your drawings has been checked against the capacity of the various bearing positions and a summary of this information is included on our drawings F.1068.B Issue 2; and F.1068C Isssue 1; copies of which we enclose

Bristol Aeroplane Company Limited. Stress Department 5216SR/16. Letter to Ransome & Marles Bearing Co Ltd NewarkTechnical Department: Re. Olympus 551 Starter, Sunstrand and fuel drives (outer end)  PA1716/5/11/2/488  24 October 1957

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Ref: 5216SR/16. Further to our letter of the 18th instant enclosing a copy of our Scheme MS.2736, will you please note that the bearings at position K and Y have now been changed to your LEJ.10 type ie. the lips will be on the inner track

Bristol Aeroplane Company Limited. Stress Department 5216SR/16. Letter to Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 551 Sunstrand and hydraulic pump drives  PA1716/5/11/2/489  30 October 1957

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Ref: 5216SR/16. Further to your letter of the 18th instant (ref: CE/SWM/KC/9347) we are enclosing a copy of our scheme RS.2736 sheet 2, which illustrates the remainder of the Sundstrand drive and gives the bearings operating conditions. The only portion of these accessory drives not completed is the LP tachometer drives, and this will be forwarded in due course when the design is complete

Bristol Aeroplane Company Limited. Stress Department 5216SR/16. Letter to Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 551 Starter, Sunstrand and hydraulic pump drives (outer end)  PA1716/5/11/2/490  18 November 1957

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Ref: 5216SR/16. Thankyou for your letter and attached data-sheets of the 12th instant, from which it is noted that you consider the bearings satisfactory. With regard to remarks on bearings at position N and R, we shall be retaining them as shown on our Scheme as position N and then be identical to position D in the inner end drive, and position R cannot be reduced on outside diameter due to the adjacent seal

Bristol Aeroplane Company Limited. Stress Department 5216SR/16. Letter to Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 551 Sunstrand and hydraulic pump drives  PA1716/5/11/2/491  25 November 1957

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Ref: 5216SR/16. We thank you for your letter and attached data-sheet 139 together with with sheet F.1068.B, from which it is noted you consider the bearing satisfactory. The information has been passed to the Drawing Office and you should receive copies of our drawings in due course

Bristol Aeroplane Company Limited. Stress Department 5216SR/16. Letter to Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 551 accessory drives  PA1716/5/11/2/492  13 January 1958

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Ref: 5216SR/16. CE/SWM/KC/9635. Further to our letters of the 26th september and 22nd November 1957, these drives have been modified to incorporate an American fuel system instead of our standard Lucas system. This has involved some redesign as follows: MS.2701. On your copy of this Scheme, will you please delete the loads and speeds and add this note; 'Loads and speeds are given on MS.2736 sheet 4'. The bearings remain unchanged. MS.2736 sheet 1. This sheet has now been cancelled and the new drives are shown on sheets 3 and 4, which are enclosed with this letter for your attention. MS.2736 Sheet 2. On your copy od this sheet, will you please delete the loads and speeds and add this note: 'Loads and speeds are given on MS.2736 sheet 4'. It is unfortunate that these changes have been required after we have both completed all the technical work on the drives and we regret the inconvenience you have been caused. However, if you could help us once more by clearing these new schemes at an early date, it would of great assistance, as our drawing office is most anxious to clear the details with America

Bristol Aeroplane Company Limited. Stress Department 521D/19. Letter to Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 22R derivation drive for Dowty vapour-core reheat pump  PA1716/5/11/2/493  12 November 1959

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Our ref: EW-D/KBC/11958. In order that components for the Olympus 22R engine may be tested in advance, we are proposing to use the existing Olympus 200 engine suitably modified. One of the first items to be tested is the above Dowty pump, which it is anticipated will be ready at the end of the month. A copy of our Scheme MS.3195 is enclosed showing the installation of this pump on one of the accessory drive faces of a 200 engine, and you will see that the only new bearing required is an XXJ.40. This bearing has been specified by the designer as FBS.245/40/AD, but we are wondering if you will be satisfied with this in view of the high speed and virtually 'no-load' running condition

Bristol Aeroplane Company Limited. Stress Department. Letter from Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 22R derivation drive for Dowty vapour-core reheat pump  PA1716/5/11/2/494  20 November 1959

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Our Ref: Tech/LEH/KH/508. Your ref: EW-D/KBC/11958. SR521D/19. We thank you for your letter of November 12th with scheme MS.3195, and note you would like to have our comments regarding the bearings selected. The remainder is technical details of the project

Bristol Aeroplane Company Limited. Stress Department 521D/19. Letter to Ransome & Marles Bearing Co Ltd Newark Technical Department: Re. Olympus 22R derivation drive for Dowty vapour-core reheat pump  PA1716/5/11/2/495  25 November 1959

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Your Ref: Tech/LEH/KH/508. Our ref: EW-D/KBC/11958. SR521D/19. The bearing XXJ.40 will be used in the test engine only and not in the Olympus 22R itself. Therefore it will not be necessary to have any of these bearings in BACE.173. We do, however, agree that as the tendency is for loads, speeds and temperature of accessory bearings to increase, consideration should be given to specifying future bearings in BACE.173

Bristol Aeroplane Company Limited. Stress Department 521D/22. Memo from KB Chamberlain to Mr HF Rodgers Cat 'I'Olympus 200 strengthened starter drive 03S.3297.  PA1716/5/11/2/496  24 May 1960

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Our ref: EW-D/KBC/14096. SR521D/22. Your ref EW-D/KBC/2730. We have examined the above scheme and find that the starter drive to basic schemes 03S.460/1 and 03S.924 is satisfactory for the following conditions when schemes 03S.3004 and 3297 are incorporated. Technical details in rest of memo

Rolls-Royce Bristol Engine Division: Olympus 200/300 series engines. Overhaul and strip rebuild schedule OSR No.1  PA1716/5/11/2/497  December 1968

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Approved LTC July 19th 1968 - Item 1886

Bristol Aero Engines (Gas turbines) Engine stress investigation: Olympus MK.551 starter & accessory drives. Stressing of stationery parts  PA1716/5/11/2/498  26 March 1958

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Ref: 521/SR17. Scheme drawings used 03S2025, 03S1955, 03S1872, 03S1961, 03S1951. 43-page report with stress calculations

Bristol Aero Engines (Gas turbines) Engine stress investigation: Olympus MK.551 inter case drives. Provisional drive ratingd (for installational DR6)  PA1716/5/11/2/499  13 March 1958

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Ref: 5216SR/18. Scheme drawings used: 03S1872, 1951, 1955, 1961, 2025. Previous calculations: 5216SR/14, 5216SR/15, 5216SR/17. Page 1: Tabled information (isued to Technical Records). Pages 2-4: Bearing load sheets for cases other than as 5216SR/15

Bristol Aero Engines (Gas turbines) Engine stress investigation internal memo SR521D/20: Olympus strengthened hydraulic pump drive & quill shafts with shear neck failing torques  PA1716/5/11/2/500  5 January 1961

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Our ref EW-D/HFR/2641. Internal memo from HF Rodgers to Mr K Chamberlaine Stress Office: Strengthened hydraulic pump drive & quill shafts with shear neck failing torques of 4784 lb/in and 3500 lb/in. 4129 lb/in and 2963 lb/in. 03S3292 Issue.1

Bristol Aero Engines (Gas turbines) Engine stress investigation SR521D/20: Olympus 201 hydraulic pump drive 13/23 bevels (8.75 DP)  PA1716/5/11/2/501  10 January 1961

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Scheme drawings used: 03S3292. Full treatment SM74 and modified SM71 calculations of bearing stress to balance tooth thickness. Page 1: Calculation basis and summary of bend stress. Pages 2-3: Initial calculations (basic proportion) of 8.75 DP bevels. Pages 4-21: SM74 & SM71 tables for 8.67 DP bevels. Page 22: Determination of entries for 8.75 bevels in GDS400. Page 23: Copy of detail DOs; GD5400 sheet 10 of calculations.

Bristol Aero Engines (Gas turbines) Engine stress investigation SR521D/20: Olympus 201 hydraulic pump (strengthened) bevel gears. Non-standard features of 15/31/15 bevels detailing data  PA1716/5/11/2/502  12 January 1961

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Scheme/drawings used 03S3292. Data referred to GDS400

Bristol Aero Engines (Gas turbines) Engine stress investigation SR521D/20: Olympus 201 Dowty Super Vardel hydraulic pump. Pump shaft. To determine the failing torque of this shaft & to compare this with figures received from Dowty  PA1716/5/11/2/503  27 February 1961

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Schme/drawings used: Dowty Drawing A.8032.Y.6

Letter from Bristol Aero Engines (Gas turbines) Engine stress investigation Department SR521D/20 to Dowty-Rotol: Olympus 201 series engine. Shearing torque for engine drive to hydraulic pump  PA1716/5/11/2/504  15 February 1961

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Our ref EW-HFR/2677. Letter from HF Rodgers Assistant Chief Designer, production Engines Bristol Siddeley Engines Limited: We are at present investigating an increased strength engine drive to prevent fatigue failures which have occurred on the shear neck in the engine to the Super Verdal hydraulic pump. In order that we may accurately assess the optimum diameter for the stronger shear neck, we will be pleased if you would send us a detail drawing of the pump shaft for stress evaluation since we understand this shaft to be the weakest part of the pump itself

Bristol Aero Engines (Gas turbines) Engine stress investigation. From Development 'D' DepartmentSR521D/20: Olympus 201 failure report on the hydraulic pump drive bevel gear housing form Olympus 201 engine No.600275  PA1716/5/11/2/505  4 February 1964

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Olympus No.600275 was returned from RAF Conings by for suspected metal fragments in the pump. The engine was rejected following an investigation which showed that after a quill failure, part of the quill was missing. This quill is the breaking or shear quill for the hydraulic pump drive

Bristol Aero Engines (Gas turbines) Engine stress investigation. Department SR521D/20: Olympus 200 & 300 series hydraulic & pump drive (stiffened) shafts, serrations & gears  PA1716/5/11/2/506  21 April 1961

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Scheme/drawings used: 03S460/1&4, 03S3292. Pages 1-13 Diagrams and tables to SM60. Calculations by RSL Pritchard

Bristol Aero Engines (Gas turbines) Engine stress investigation. Department SR521D/20: Stress summary. Olympus 200 & 300 series HP rotor hydraulic & oil pump drive (stiffened)  PA1716/5/11/2/507  April 1961

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Scheme Nos: 03S460/1, 03S460/4, 03S3292. Front sheet plus 10 sheets to SM63. Note! Bearing criteria has been obtained by proportioning existing summary (SR521D/9 & 11) values. This does not take into account the slight differences in mid-face width position of the new 15/31/15 & 13/43 bevels, but this effect is small. Inner end spur gear criteria has also been predetermined from existing summary. Gear & SC's do not allow for MT52 (i.e.as exists Sim for 03S5495 etc.)

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department SR521D/20: Stress summary. Olympus 200 & 300 series hydraulic & oil pump drive. Gears and shafts. Comparison of ULT torsion factors  PA1716/5/11/2/508  18 May 1961

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Standard drive with 1880 lbs/in shear neck stiffened drive with 3000 lbs/in shear neck and changes to standard drive to use 3000 neck. Scheme/drawings used: Standard drive 03S495, 03S2555; 03S3292 stiffened drive. Previous calculations 521D/20 of 21/4/6. Pages 1 & 2: basis of calculations. Page 3 Shaft factors & gear SFs. Page 4 Shaft and gear factors. Page 5 Changes required to standard drive to take 3000 neck

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department SR521D/20 internal Memo: Olympus 200 & 300 series. Pre-formed roots for fuel pump drive inner end spur gears  PA1716/5/11/2/509  3 May 1961

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Internal memo from Mr KB Chamberlain, Stress Department to Mr HF Rodgers & Mr FW Allard. Attached print of MS3486 covers the specification of tooth form for these gears

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department SR521D/21: Olympus Mk.200 & Mk.300. LP fuel pump drive 44/47 preformed root spur gears  PA1716/5/11/2/510  5 April 1961

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Detail dimensions and stressing for 44/47 spurs by Device Programme 17073. Scheme/drawings used: MS3486; 03S3491. Page 1: Device entry sheet. Page 2 Calculations of kp & kw to suit existing [ ] Page 3 Choice of kp or kw. Pages 4-9: Device results SEE MS3503 & SR0107/109 for key for device results

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department SR521D/21: Olympus Mk.200 & Mk.300. LP fuel pump drive 44 preformed root spur pinion.  PA1716/5/11/2/511  3 May 1961

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Detail dimensions and stresses for 44/47 spurs by Device Programme 17073 - 48 wheel in existing part which does not have pre-formed roots. Scheme/drawings used: 03S3473

Letter from Ransome & Marles Bearing Co Ltd to Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department SR5216/22: Olympus Mk.201 & MK.301 strengthened starter drive (outer end)  PA1716/5/11/2/512  25 April 1961

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Ransome & Marles ref: Tech/LEH/KH/11445. Our ref EW-D/KBC/13981

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department SR521D/22 internal memo: 03S.3297 Issue 2. Strengthened starter drive (outer) using existing parts  PA1716/5/11/2/513  26 April 1961

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Internal memo from Mr HF Rodgers to Mr KB Chamberlain Stress Office. Includes related diagram

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department SR521D/22. Olympus Mk.200 starter drive. Driving quill and sundstrand bevel stiffened version of above components  PA1716/5/11/2/514  12 May 1961

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Ref: SR521D/22. Sheme/drawings used: 03S.460/1, 03S.924, 03S.3297. Contents: 1-16. Tables to SM63 calculations. 17-18. Gear tooth stresses from previously calculated facors. 19-20 Checking of ULT factors, working stresses and serration bearings pressures as printed on 03S.3297. Note! All torsion sections, splines and gear tooth streses, and one pair of bearings are calculated here. Other values required for 03S.3297 summary have been proportioned from existing summary SR521D/9 & 10 of January 1957. Where cross-checks can be made, values calculated here give agreement with existing summary values factored for torque increase

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department. Stress summary SR521D/22. Olympus Mk.200 starter drive (stiffened)  PA1716/5/11/2/515  May 1961

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Scheme Nos. 03S.460/1; 03S924; 03S.3004 (calls for 46 layshaft gear in BACE.366); 03S.3297 (Strengthened radial quillshaft). Front sheet plus 8 shets to SM63

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department. Stress summary SR521D/23. Olympus Mk.301 starter ratchet and pawl. Stressing of pawl at starter shearneck torque (at various depths of critical section)  PA1716/5/11/2/516  September 1961

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Scheme/darwings used: 03S.3458. 5 pages of calculations

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department. Stress summary SR521D/23. Olympus MK.200 & 301 starter ratchet and pawl. Pawl CG position & weight of pawl. For 'rapid start' increased operation speed pawl & polar Maf.1 about pawl pin centre  PA1716/5/11/2/517  12 October 1961

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Scheme/drawings used: 03S.3458 pawl; B120209 (pawl carrier); MS.3636. Page 1: Pawl dimensions. Page 2: Pawl CG postion & WT. Pages 3-7: Areas and movements of area of pwl sections, tabular calculations. Pages 8-9 Graphs. Page 10: Graph integrating M/C bearings and calculations of areas of movement. Added 26 March 1962: Page 11: Tabulation for measure and plot method for polar Mof1 about pawl centre. Page 12: Graph. Page 13: Calculations of polar Mof1about pawl pin centre. Pages 14-16: Graphical integration M/C readings for 2nd movement of area.

Bristol Aero Engines (Gas turbines) Engine Stress Investigation Department. Stress summary SR521D/23. Olympus MK.200 & 301 starter ratchet and pawl. Pawl spring. Determining from experimental data of spring load required to operate pawl (new design to 03S.3458) at 2300-2400 HP rotor rpm and design of spring to give this load  PA1716/5/11/2/518  30 November 1961

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Scheme/drawings used: 03S.3458, B.109266 (pawl carrier); B176363 Pawl); MS3659 (Pawl and spring layout); MS3659 (pawl balancing); MS3632 (pawl). Previous calculations: SR521D/23 12 October 1961; MRD report No.898/60; File No. 521D/10. Page 1: Introductory note and summary of data for chosen spring. Page 2: Nomenclature. Page 3: Experimental data from MRD report 898/60. Pages 4-5: Calculations of friction coefficient from above data. Page 6: Experimental data from MRD test on pawl to 03S.3458. Page 6: Required spring load calculated from all above data. Page 7: Calculations for spring to give required load (design and stressing). Page 8: Stress in existing spring B109266 on stop with existing pawl B176363. Also as used in MRD test (Page 6).

Bristol Siddeley Engines Limited. System Performance Department. Stress Investigation Ref: PDM 3957. Olympus 200 series and 301 oil feed to the top serrations on the starter drive  PA1716/5/11/2/519  11 November 1966

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it is required to lubricate the top splines on the starter drive of the Olympus 200 series and 301 engines in order to prevent fretting (Design Office scheme 03S.4403)

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/23. Olympus Mk301 starter ratchet and pawl. Pawl Investigation of the effect of modifiations of pawl profile on ratcheting loads (due to pawl inertia only) between ratchet tooth and pawl  PA1716/5/11/2/520  26 April 1962

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Scheme/drawing used: 03S.3458/2; B176363 existing pawl; Layout MS.3729 & MS.3730. B120209 pawl carrier. B120208 ratchet shaft. Previous calculations: SR521D/23 12 October 1961

Bristol Siddeley Engines Limited internal memo from Engine Stress Development 'D' Olympus Section. SR521D/23. Olympus .Mk301, 201, 21A & B. Design scheme Request No.2168. New scheme for the Starter drive ratchet mechanism similar to 03S.3458  PA1716/5/11/2/521  10 July 1962

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Internal memo from Development 'D' Department to Messrs H Rodgers, Henley, Evans, Woodward & Beauchamp

Bristol Siddeley Engines Limited internal memo from Experimental Inspection Department Engine Stress SR521D/23. Temperature paint report No.37/62. Rotax combustion type starter-type CT.0818 Exp.4 Olympus Mk301 OL.2105 (on test)  PA1716/5/11/2/522  18 July 1962

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Brockwoth Test Department personnel applied temperature sensitive paints to the outer surface of the starter. Report on page 2

Bristol Siddeley Engines Limited internal memo from Experimental Inspection Department Engine Stress SR521D/23. Temerpature paint report No.41/62. Rotax combustion starter insulation blanket ex Olympus 2113  PA1716/5/11/2/523  23 August 1962

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The temperatures recorded by the paints are shown of the attached sketch

Bristol Siddeley Engines Limited internal memo from Development 'D' Department. Engine Stress SR521D/23. Olympus 201/301 engines. Minutes of a meeting held in Development Engineers Department on 3 October 1962 on starter drive for rapid starting  PA1716/5/11/2/524  3 October 1962

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Bristol Siddeley Engines Limited. Olympus engine stress SR521D/23: Internal memo from J Mead EW-D/JM to LH Granfield. Spring B.237204 (03S.3458) Olympus 300 starter pawl  PA1716/5/11/2/525  8 November 1962

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Contents:
The above specifies DTD.215 material

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/23. Olympus .Mk301 starter ratchet and pawl. Pawl spring. Reduced stress pawl sping in rectangular section wire (6 coils) for rapid starter  PA1716/5/11/2/526  6 December 1962

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Scheme/drawings used: 03S.3754; MS.3888 (layout). Previous calculations: SR521D/23 30 November 1961

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/22. Tests on Olympus 200/300 starter mechanism  PA1716/5/11/2/527  30 July 1963

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MRD report 1283/62. A requirement for the Olympus 200/300 engine, fitted with rapid starting, is that it must be operational within 15 seconds

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20: Internal memo re. Olympus 200/300 series. Stiffened hydraulic pump drive 03S.3292. 15-tooth bevel follower Item 13 (B.226521)  PA1716/5/11/2/528  4 March 1964

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Contents:
Ref: PFG/DRE/18,366 Stress Departmnt Mr DR Evans to Mr F Allard

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Report MRD.1854/64: Summary of B.0L.301 hydraulic pump drive. Frequency survey of new and old standard bevel wheels  PA1716/5/11/2/529  19 February 1964

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Contents:
Two failures had occurred on the original standard bevel wheel and as these had fatigue cracks at the tooth roots, a new standard was designed with a wider, stiffer tooth (ie with a 8.75 dp instead of 10.0 dp)

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Report MRD.1854/64: Olympus 200 & 300 series. Hydraulic pump drive. Bearing Loads with 23-tooth bevel lengthened quill  PA1716/5/11/2/530  5 March 1964

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Contents:
Scheme/drawings used: 03S.3947 (new bearing arrangement); 03S.3292 (basic stiffened drive). Previous calculations: SR521D/20 10 January 1961 for bevel data

Report from Dowty-Rotol Limited to Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Genral test report No.12022 Addendum 13. Hydraulic pump Super Vardel Type 08032.Y.C08. Tested to determine the oscilliary input torque characteristics  PA1716/5/11/2/531  15 January 1964

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Contents:
All pumps conform to the general standard for this type of unit. This is a 5-page report

Bristol Siddeley Engines Limited. Engine Stress Investigation Department Filton. From Department 'D' SR521D/20. Minutes of meeting on Olympus 200 series & 301 oil and hydraulic pump drive failures  PA1716/5/11/2/532  23 January 1964

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Contents:
Review of failures to date. The two types of quill shaft failure (torsional shear and fatigue) give a failure rate of 1.25 per 1000 engine/hydraulic pump hours, without the hydraulic accumulator fitted and 2.67 per 1000 engine/hydraulic hours, with the hydraulic accumulator fitted. Service department stated that the hydraulic accumulators were now fitted to 22 Service aircraft, but the total hours was only 4000 to date. It was not considered that this was sufficient to determine a genuine failure rate

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Olympus 200 & 300 series. Stiffened hydraulic pump drive 03S.3292. Relative strengths through the drive at hydraulic failure conditions are as follows:  PA1716/5/11/2/533  10 March 1964

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Contents:
Internal memo from Ref: D R Evans (Stress Department) PFG/DRE/18386 to JL Norton & GH Beauchamp

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Olympus 301 hydraulic pump drive; gears and shafting. Summary of stresses for existing production standard & strengthened drive & proposal for new shearneck torque of 2400 lb/in.  PA1716/5/11/2/534  May 1964 - 6 November 1964

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Contents:
Scheme/drawings used: 03S 460/1, 03S460/4, 03S/495/64, 03S 3004, 03S 2551, 03S 3292. Previous calculations: SR521D/20, 21 April 1961; & stress summaries 4 February 1964. Summary: Pages 1-2. Page 3 Notes on sources of summary values. Page 4 Fatigue properties. Page 5 Gear tooth stresses. Page 6 -7 Fluctuating stress limits for gear teeth. Page 8 Limiting torques for fatigue of shearnecks. Page 9 Design of S/N for 2400 lbs/in & -+ 560 lbs/in fatigue. Below added 16 November 1964 Page 2a Dowty Rotol tooth stress on Buccaneer box with same pumps. Page 3a Dowty Rotol Vardel pump shaft strength. Page 4a Dowty Rotol neck strength on Buccaneer box.

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Olympus 200/300 hydraulic pump drive; inner end meeting bracket (bolts, dowels, casing)  PA1716/5/11/2/535  8 March 1966

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Contents:
From determining loading to find bearing press at dowel casing and find shear stress in thread of bolt (stud) holes in mounting bracket. Scheme/drawings used: Existing arrangement UB.122639 (bracket UB164567, stud UBS.21). New scheme: 03S4298 - bots AS.6316 (with wire insert) 03S4310. Previous calculations: Stiffened drive calculations for stressing cases used

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Olympus 300 hydraulic (stiffened) pump/sump/intercasing  PA1716/5/11/2/536  24 November 1965

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1 To compare OL.104 & OL.200/300 hydraulic pump. 2 To calculate stresses in sump/intercase studs. In both cases, unbalanced loads are considered). Scheme/drawings used: B.329247, UBS.21/F13, UB.256845. Dowty drawings: A.80003Y1, 08032Y156.

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Memo from Chief Planning Engineer (Repair) to Mr R Smith: Olympus oil pump drive (outer) B.260284  PA1716/5/11/2/537  25 October 1965

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Contents:
Arrange to check the 'gear setting distances.'

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Development 'D' Department: Olympus 200/301 series engine. Summary of strain gauge pressure results taken at Dowty Rotol Limited  PA1716/5/11/2/538  8 February 1965

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Contents:
Ref: PFG/JAW/26474

Bristol Siddeley Engines Limited. SR521D/20. Olympus 200 & 301 series engines  PA1716/5/11/2/539  1964

Bristol Siddeley Engines Limited. Memo from D R Evans Stress Investigation Department. SR521D/20. Olympus 200 & 301 series engines. Hydraulic pump drive  PA1716/5/11/2/539/1  21 May 1964

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Contents:
Ref: PFG/JAW/18809. Ref memo from PFG/JAW/14287 from Development 'D' Department re. attached stress summary sheet attached to PA1716/5/11/2/539

Bristol Siddeley Engines Limited internal Memo from D R Evans Stress Investigation Department. SR521D/20. Olympus 200 & 301 series engines. Hydraulic pump drive  PA1716/5/11/2/539/2  21 May 1964

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Contents:
From D R Evans Stress Department RefPFG/DRE/18809

Bristol Siddeley Engines Limited internal Memo from D R Evans Stress Investigation Department. SR521D/20. Olympus 200 & 301 series engines. Stiffened Hydraulic pump drive 03S.3292 13/15 tooth bevel cross-shaft  PA1716/5/11/2/539/3  8 May 1964

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Contents:
This memo explains what is involved to replace the existing parts

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Development 'D' Department: Olympus 200 & 301 series engines. Decisions taken at a meeting concerning the hydraulic and oil pump drive  PA1716/5/11/2/539/4  21 May 1964

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Contents:
Ref: PFG/JAW/14800

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Development 'D' Department: Olympus engines. Minutes of a meeting held between MoA and BSEL on 31 July 1964 to discuss merits of strengthened hydraulic and oil pump drive for Olympus 200 & 301 series engines  PA1716/5/11/2/540  13 May 1964 - 10 August 1964

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Contents:
Ref: PFG/JAW/17917

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Development 'D' Department: Olympus 200/301 series engine. Modification submission of strengthened hydraulic and oil pump drive  PA1716/5/11/2/541  11 August 1964

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Contents:
Ref: PFG/JAW/17964

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Report by Development 'D' Department: Olympus 200/301 series engine. Hydraulic and oil pump drive  PA1716/5/11/2/542  7 May 1964

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Contents:
Ref: PFG/JAW/14287. A chart is attached summarising the different types of failure experienced on service engines

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Olympus 200/301 series engine. Stiffened hydraulic and oil pump drive 03S.3292. The relative strengths through the drive at hydraulic pump shear neck failure condition are as follows...  PA1716/5/11/2/543  10 March 1964

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Contents:
Ref: PFG/DRE/18386. The details are on this tabulated sheet

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Report from Development 'D' Department: Olympus 200 & 301 series engine. Failure report on two starter rives (inner) gear mounting bracket on Mk.301 development engines OL.2113 Build 15; and OL.2109 Build 19  PA1716/5/11/2/544  7 July 1964

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Contents:
Ref: PFG/JAW/15473

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Report from Development 'D' Department: Olympus 200 & 301 series engine. Failure report Review of spline wear defects in Olympus 200 & 300 starter drives  PA1716/5/11/2/545  13 July 1964

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Contents:
Ref: PFG/JAW/15473

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/23. Olympus Mk.301 pneumatic starter pawl spring. Torsional stress in spring etc.  PA1716/5/11/2/546  29 July 1965

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Contents:
Scheme/drawings used: B.275510

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/23. Olympus Mk.301 pneumatic starter pawl. Pawl with modfied contacting profile to reduce impact load  PA1716/5/11/2/547  4 August 1965

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Contents:
Stressing of the above pawl at starter shearneck torque and determination of depth of section to maintain stress level as existing pawl. Previous calculations: SR521D/23 September 1961

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Olympus Mk.300 Hydraulic pump drive. Shear neck stress for Beryl-Copper neck for Vickers hydraulic pump  PA1716/5/11/2/548  18 February 1966

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Contents:
Scheme/drawings used: 03S.4297

Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/22. Defect report by Development 'D' Department. Addendum to Review of spline wear defects in Olympus 200/301 series starter drives (Refer to PFG/JAW/33335 Dated 13 July 1965)  PA1716/5/11/2/549  3 August 1965

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Contents:
Ref: PFG/JAW/34023

Letter to Dowty Rotol Limited from Bristol Siddeley Engines Limited. Engine Stress Investigation Department. SR521D/20. Olympus in Vulcan. Type Test of Super Vardel Hydraulic pump. Type 1,00025.069 Issue 1 with balanced weight deleted  PA1716/5/11/2/550  15 December 1965

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Contents:
Ref: PFG/JAW/30753. For the attention of Mr Morris. The above pump (Serial No.CP/DRG/95/65) has recently completed a 150-hour endurance test on our engine OL.2105 Builds 20 & 21at Brockworth. The total running time of the pump was 172 hours. A schedule giving a large number of on/off cycles was imposed as agreed with you

Internal memo from Vibration Department Bristol Siddeley Engines Limited to Engine Stress Investigation Department: SR521D/22. Olympus 301 frequency checks in starter drive ratchet  PA1716/5/11/2/551  24 September 1965

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Contents:
Ref: PFG/EKA/16851. Due to failure of the above component, frequency checks were initiated, (See TP.6169 and TP.6367) on Units to B120208 and B331843, the latter being a strengthened design in accordance with 03S.4041. The natural frequencies in cycles per second below...

Internal memo from Stress Department Bristol Siddeley Engines Limited to Mr Beauchamp. SR521D/23: Olympus 301 starter ratchet. Investigation of suitable pawl spring load for new spring checking fixture  PA1716/5/11/2/552  13 April 1966

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Contents:
Ref: PFG/DRE/21637. Four-page report

Bristol Siddeley Engines Limited. Engine Stress Investigation report: Olympus SR521D/23. 301 starter ratchet. Starter ratchet assembly. Assessment of spring load to operate pawls at 5000 carrier rpm  PA1716/5/11/2/553  21 April 1966

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Contents:
Scheme/drawing used: Pawl B237203, Spring B275510, MS.3888. Previous calculations: SR521D/23 30 November 1961, 6 December 1962

Bristol Siddeley Engines 554 Limited. Engine Stress Investigation SR521D/22: Report from Development Department No.565B - Olympus 200 series/301. Starter drive inner spur gear B151361 and B315467  PA1716/5/11/2/554  16 September 1966

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Contents:
Ref: PFG/GHB/48177. Re-issued

Bristol Siddeley Engines 554 Limited. Engine Stress Investigation SR521D/22: Report from Quality Observers' Office - Olympus 200 series/301. Starter drive inner spur gear B151361 and B315467  PA1716/5/11/2/555  6 October 1966

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Ref: EE/RRWS/AMA/HMB

Bristol Siddeley Engines Limited. Engine Stress Investigation Mechanical Research Department: Compressor strain gauge report. Olympus 301 Datum test prior to an intended motorised throttle test. Titanium alloy 'O' stage rotor blades. Engine No.2106 Build 11  PA1716/5/11/2/556  14 July 1964

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Contents:
Ref: PFG/GW. MRD Report 1920/64

Bristol Siddeley Engines Limited. Engine Stress Investigation Mechanical Research Department: Compressor strain gauge report.  PA1716/5/11/2/557  14 July 1964

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Bristol Siddeley Engines Limited. Engine Stress Investigation Mechanical Research Department: Compressor strain gauge report.  PA1716/5/11/2/558  14 July 1964

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Contents:
Olympus 301 vibration of standard 9.5deg fine aluminium alloy 'O' rotor blades (with +2deg IGV) during low level, high-speed flight. Engine No.2111(18) in No.1 position in Vulcan B.Mk.2 (XH557). Ref: PFG/GW. MRD report No.1919/64. Violent 'O' stage flutter in the 1F at altitudes below 1,000 ft and at 330 knots at 10,000 ft

Bristol Siddeley Engines Limited. Engine Stress Investigation Mechanical Research Department: Compressor strain gauge report. Olympus 301 in Vulcan B.Mk.2 (XH557) during low level, high-speed flight. Engine No.2112 Builds 16 (-2deg IGV) & 17 (standard 9.5 deg fine 'O' stage rotor blades with LPIGV's at both -2 and +2)  PA1716/5/11/2/559  26 August 1965

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Contents:
MRD report No.1982/64

Bristol Siddeley Engines Limited. Engine Stress Investigation Mechanical Research Department: Compressor strain gauge report. Olympus 301 1st Stage (HP)  PA1716/5/11/2/560  14 July 1964

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Bristol Siddeley Engines Limited. Engine Stress Department report 1002: Olympus 300 No.2117. Vibration of valve in double datum unit  PA1716/5/11/2/561  15 February 1967

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Bristol Siddeley Engines Limited. Engine Stress Department: Mechanical Research Department. Turbine strain gauge report 2488/67 - Olympus 300 1st stage HP rotor blades in MRE 2 (6, 7, 8). Stator gap variation, loss of CC swirler, loose disk bolts  PA1716/5/11/2/562  24 February 1966

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Bristol Siddeley Engines Limited. Engine Stress Department report SV73: Rig testing of Industrial Olympus No.4 bearing 'Pot scrubber' mounting  PA1716/5/11/2/563  10 March 1967

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Contents:
Ref: PFG/DRE/23,258. The basic purpose for the fitment of such a device is to reduce the force applied to the casing from the HP system lateral movement. This can arise from two factors primarily...

Bristol Siddeley Engines Limited. Engine Stress Department. Mechanial Research Department report 2609/67. Compressor strain gauge report. 'O' and 4th stage LP compressor stators. Olympus 301 Engine No.2117 Build 28  PA1716/5/11/2/564  25 September 1967

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Contents:
Ref: PFG/EKA

Bristol Siddeley Engines Limited. Engine Stress Department. Mechanial Research Department report 267/67. Turbine strain gauge report. HP disk investigation endurance test. Olympus 301 engine MRE.2 Builds 12 & 13  PA1716/5/11/2/565  29 September 1967

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Contents:
Ref: PFG/EKA

Bristol Siddeley Engines Limited. Engine Stress Department. Mechanial Research Department report 2768/67. Turbine strain gauge report. Olympus 301 disk and blade with swirler blockage test. 301 engine MRE.2 Build 14 wheel 7  PA1716/5/11/2/566  19 October 1967

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Contents:
Ref: PFG/EKA. Summary: This investigation was a strain gauge survey of the 'O' and 4th stage LP compressor ststors. Service failures have occurred on the 'O' stage blades

Bristol Siddeley Engines Limited. Engine Stress Department. Mechanial Research Department report 2768/67. Summary of results of testing Olympus 609. (MRE.1) HP single spool engine Builds 18-32. Olympus MRE.2 HP single spool engine Builds 1 & 2  PA1716/5/11/2/567  28 July 1967

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Ref: PFG/EKA. Report written December 1965. During the six years, approximately, that Olympus Mk.301 engines have been running (3.5 years in service) there have been about ten fatigue failures of the 1st stage (HP) turbine rotor blades

Bristol Siddeley Engines Limited. Engine Stress Department. Mechanial Research Department report 2748/67. Turbine strain gauge report. Olympus 301 super thick HP turbine disk with stator blockage (Build 39) and cooled stators (Builds 40, 41) Olympus 301 engine MRE.1 Builds 39, 40 & 41  PA1716/5/11/2/568  18 March 1968

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Contents:
Ref: pfg/GW/EKA

Bristol Siddeley Engines Limited. Engine Stress Department. Mechanial Research Department report 2895/67. Turbine strain gauge programme. Olympus 301 HP turbine rotors with controlled shroud gaps. MRE.1 Build 44 (standard disk)  PA1716/5/11/2/569  12 September 1968

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Contents:
Ref: PFG/EKA/20,886. Issued by Vibrations Engineering Department (MRD). 62756

Rolls-Royce Limited. Bristol Engine Division. Engine Stress Department. Mechanial Research Department report 2870/68. Turbine strain gauge report. 1st HP turbine rotor with wirelaced blades (standard disk) Olympus 301 Engine MRE.2 Build 16  PA1716/5/11/2/570  30 September 1968

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Contents:
Ref: PFG/GW/EKA. Contract report MRD2870/68. Nine-page report

Rolls-Royce Limited. Bristol Engine Division. Engine Stress Department. Mechanial Research Department report 2895/68.Turbine strain gauge report. Olympus 301 HP turbine with combustion chamber flare blockage. MRE.2 Engine Build 17  PA1716/5/11/2/571  16 October 1968

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PFG/GW/EKA. Contract report MRD/2895/68. A combustion flare failure has occurred on an Olympus 301 engine. The flare piece which was curled up at one end, had broken loose and become lodged against the side of the turbine entry duct of the No.2 can. The engine was thought to have run for about 8 hours before the failure discovered

Rolls-Royce Limited. Bristol Engine Division Coventry. Engine Stress Department. Mechanial Research Department report 1015/68. Frequency survey report (OLY 201, 301). Frequency survey of a pair of 1st stage turbine blades joined together at the shroud  PA1716/5/11/2/572  18 December 1968

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SV.73. Work carried out during January and February 1968. Fatigue failures of Olympus 1st stage turbine blades have occurred in Service engines

Rolls-Royce Limited. Bristol Engine Division Coventry. Engine Stress Department 64069. Vibration Engineering (MRD) 1st HP with super thick disc and production aero standard blades MRE.2 Build 22  PA1716/5/11/2/573  6 March 1969

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Contents:
Ref: PFG/GW/EKA/21,378

Rolls-Royce Limited. Bristol Engine Division Coventry. Engine Stress Department 64025. Turbine strain gauge programme. Issued by Vibration Engineering (MRD). 1st HP with interlocking shrouds (super thick disc). MRE.1 Build 46  PA1716/5/11/2/574  12 March 1969

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Contents:
Ref: PFG/GW/EKA/21,390

Rolls-Royce Limited. Bristol Engine Division Coventry. Engine Stress Department 64173. Turbine strain gauge programme. Issued by Vibration Engineering (MRD). Industrial 1st HP with industrial flame tubes. MRE.1 Build 45C  PA1716/5/11/2/575  11 April 1969

Contents:
Ref: PFG/GW/EKA/21,455. Since the introduction of Industrial Standard flame tubes into IMD engines, there has been a significant increase in the failure rate of the 1st stage HP blades (From .045 per 1,000 hours to .195 per 1,000 hours and 4 failures have occurred in the month of March alone)

Bristol Aeroplane Company. Gas Turbines. Engine Stress Investigation 4386SR/1. Olympus Mk.21. Turbine LP stator segments. Cirumferential clearance between stator segments  PA1716/5/11/2/576  15 April 1958

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Contents:
Performance Office Data used: PDM881. Calculations by DJ Fortune attached

Bristol Aeroplane Company. Gas Turbines. Engine Stress Investigation 438DSR/3. Olympus Mk.7. Turbine HP stator segment. Cirumferential clearance between segments  PA1716/5/11/2/577  24 June 1958

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Contents:
Scheme/drawings used: 03S 2409/1, 03S 258/5. Calculations by DJ Fortune

Bristol Aeroplane Company. Gas Turbines. Engine Stress Investigation 4384SR/1. Olympus 103, & 104 turbine. Radial growths of Olympus 103 & 104 rotors and changes in shroud clearance  PA1716/5/11/2/578  May 1958

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Contents:
Calculations by P Sheath

Bristol Aeroplane Company. Gas Turbines. Engine Stress Investigation 438DSR/2. Olympus Mk.21 turbine. HP stator segment. Circumferential clearances between segments  PA1716/5/11/2/579  20 June 1958

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Contents:
Scheme/drawings used: 03S 2241, 03S 258/5. Performance office data used: GP8/58. Calculations by DJ Fortune

Bristol Aeroplane Company. Gas Turbines. Engine Stress Investigation 438DSR/4. Olympus Mk.6 turbine. Change in radial clearance at 'N' labyrinth (IE interstage labyrinth) under running conditions  PA1716/5/11/2/580  22 July 1958

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Contents:
Previous calculations: 4446AS/4 (PJS August 1957); 4426SR/6 (JA Barrett 18 July 1958). Calculations by DJ Fortune

Bristol Aeroplane Company. Gas Turbines. Engine Stress Investigation 438CSR/2. Olympus 104 HP turbine. Estimation of Changes in axial and radial clearance at HP rotor turbine rotor tip  PA1716/5/11/2/581  October 1958

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Contents:
Scheme/drawings used: OLS 3185. Previous calculations: 4444/17, 4434/20, 4434/21. Calculations by P Sheath

Bristol Siddeley Stress Department: Power plant Design Office. Jet pipe roller loads for Olympus in Vulcan Mk.2  PA1716/5/11/2/582  24 September 1958

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Contents:
Ref:CE/SWM/KC/10,529

Bristol Siddeley Stress Investigations: Engine strain gauge & rig fatigue report MRD 1166/62. Olympus 201 & 301 split feed flame tube nose cones (Olympus 2113 Build 3)  PA1716/5/11/2/583  17 April 1962

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Contents:
Ref: EW-D/GW. Following a number of failures of split feed nose cones to 03S.3135 during bench running, it was requested that rig fatigue tests should be carried out, to attempt to reproduce engine failures. In addition, two nose cones were strain gauged and fitted to Olympus No.2113 (Build 3), together with a strain gauge burner and combustion chamber straps. Pressure pick-ups were also fitted

Memo from Mr Lindsey to W.F. Wright requesting the supply of a confidential report on the Bristol Olympus to Mr Chapman  PA1716/5/11/2/584  2 February 1950

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Memo from Mr Saxon to Mr Chapman regarding the fact that the Bristol Olympus was scheduled for the A.V. Roe Bomber  PA1716/5/11/2/585  19 January 1950

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Memo from Bristol Aero-Engines to Messrs A.V. Roe and Co. regarding the Vulcan B. Mk 2 Jet Pipe Support Loads  PA1716/5/11/2/586  6 March 1958

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Bristol Engines Development Report No. 270 regarding Olympus Mark 202 Engines  PA1716/5/11/2/587  26 August 1976

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Frequency Survey Report No. MES 1563/81  PA1716/5/11/2/588  20 March 1981

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Memo regarding the Aero Olympus - Life Assessment Fatigue Tests on Compressor Rotor Blades at 2500 Hrs Life  PA1716/5/11/2/589  5 November 1979

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Report on Damping Test - Olympus Mk. 301 - Damping Characteristics of CCOC 'Belly-Brand' Damper, No. MES 1155/81  PA1716/5/11/2/590  26 March 1981

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Fatigue Test Report - Olympus 301 Compressor Rotor Blades, Life Assessment Fatigue Tests at 2500 Hrs Service Life  PA1716/5/11/2/591  15 October 1979

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Handwritten Fatigue Test Report - Olympus 301 Compressor Stator Blades Stages 1 to 7, Life Assessment Fatigue Tests at a Service Life of 2111 Hrs  PA1716/5/11/2/592  13 August 1976

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Memo from the Mechanical Development Engineer to P.F. Green regarding Proteus 755 Series  PA1716/5/11/2/593  6 January 1959

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Contents:
Rubbing probe test to measure running clearances between turbine interstage diaphragms and discs

Engine Stress Investigation on Proteus 4, 1st and 2nd Stage Turbines  PA1716/5/11/2/594  April 1958

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Photocopied extracts from 'The Jet Aircraft of the World' and 'Gas Turbines and Jet Propulsion'  PA1716/5/11/2/595  c. 1950s

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Memo from Mr Lindsey to Mr Chapman concerning the new Bristol Olympus engine  PA1716/5/11/2/596  8 February 1950

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Strip sheets concerning the Olympus 301  PA1716/5/11/2/597  4 July 1977

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Strip sheets and engine build concerning the Olympus 201 and 301  PA1716/5/11/2/598  22 June 1956

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Memo from P.F. Green to Dr. R.C. Plumb concerning the Proteus turbine blade axial clearances  PA1716/5/11/2/599  15 April 1958

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Contents:
With attached table

Laboratory Integrity Testing Reports for Olympus 200/300  PA1716/5/11/2/600  1979

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Contents:
Includes related flange temperatures graph, production drawing office instruction and handwritten note

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353SR/7: Olympus Mk.1/2C LP compressor rotor discs. Axial collapse of Mk.1/2C LP compressor rotor discs due to tightening of compressor bolts  PA1716/5/11/2/601  12 January 1953

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Contents:
Schemes/drawings used: B.23021, B.23022, B.23023, B.21187, B.21188. B.54448, B.54447, B.60266, B.60267, B.60268. Calculations of disc deflections pages 1-4. Calculations by JA Taylor

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353SR/7: Internal memo from Stress Department to Dr Hooker - Alignment of LP compressor rotor shaft Olympus 1/2  PA1716/5/11/2/602  5 February 1953

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Bristol Aeroplane Company. Gas turbines. Stress investigations 4353SR/8: Olympus Mk.1/2C LP compressor rotor discs. Stressing of LP compressor rotor discs  PA1716/5/11/2/603  30 March 1953

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Contents:
Scheme/drawings used: B.78449, B.60267-8, B.54447-8, B.23024. Previous calculations used: 4353/11, 4363/12. Calculations by DJ Fortune. For later stressing see 4353/8 1 May 1957 MS.2626

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353SR/8: Olympus Mk.1/2C LP compressor rotor discs. Stages 1-6 disc calculations with graphs  PA1716/5/11/2/604  c. 1953

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Contents:
Heading page missing

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353SR/8: Olympus Mk.102 LP compressor rotor 1st & 4th stage discs. Redesign of 1st & 4th stage discs keeping approximately the same max stresses as in the previous discs.  PA1716/5/11/2/605  26 April 1956

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Contents:
Scheme/drawing used: OLS.3506. Previous calculations 4353/8 30 March 1953. Page 1: 1st stage disc loadings and graph. Page 3: 4th tage disc loadings and graph.

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353/8: Olympus Mk.101 LP compressor rotor 1st stage disc (3 lobe root); disc stresses  PA1716/5/11/2/606  8 January 1957

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Contents:
Calculations by HGP

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353/8: Stress Clearance record. Olympus Mk.101 LP compressor rotor discs  PA1716/5/11/2/607  4 February 1957

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Contents:
Scheme OLS.3868. We have examined scheme OLS.3868 showing the redesigned 1st stage rotor disc in BRACE.210 to carry the stiffened root form blades and find it satisfactory from the stress aspect

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353/9: Engine stress investigation. Olympus Mk.104 LP compressor rotor. 1st stage disc  PA1716/5/11/2/608  8 November 1957

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Contents:
Scheme/drawings used: OLS.4228. Rim load taken from root calculations in 4353/12 of 22 October 1957. Calculations by HGL

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353/9: Engine stress investigation. Olympus Mk.1/2C compressor. 1st stage rotor blades and disc. Rotor blade, root fixing, and disc stresses with steel blades in (1) exsisting and (2) steel disc  PA1716/5/11/2/609  30 July 1953

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Contents:
Previous calculations referred to 4353/8, 4353/11,4353/12. calculations by DJ Fortune

Bristol Aeroplane Company. Gas turbines. Stress investigations 4353SR/9: Internal memo from Stress Department CE/SWM/KC/3382. Engine stress investigation. Olympus 101 LP compressor. 1st stage disc in steel to carry steel blades  PA1716/5/11/2/610  7 August 1953

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Contents:
Ref:4353SR/9. When 1st stage blades are made in steel but dimensionally the same as the existing alloy ones, the profile of the steel disc is S.96 or S.106 required to carry them the same as the existing light alloy discs ie. the new steel disc should be made to MS.1261 or B.78449

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/9: Olympus 101 LP compressor rotor. 1st stage disc in steel. Presentation of data stressing stright rotor discs on DEUCE. Programme Ref 12005/80A  PA1716/5/11/2/611  1 May 1957

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Contents:
Drawing and graph MS.2658 Olympus 101 LP compressor 2nd stage disc (alloy); Olympus 101 1st stage disc (alloy) and MS.2657

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/9: Olympus 101 LP compressor rotor. 1st stage disc design for use with Titanium blades with lobe root fixings  PA1716/5/11/2/612  1 July 1957

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Contents:
Calculations by RE Jenkins. Previous calculations 4353SR/9 of 1 May 1957; 4363/12 of 11 January 1957; and 4363/12 of 27 April 1957. For disc design refer to MS.2661 (Olyhmpus 4133) attached. Presentation of data for stressing straight rotor discs on DEUCE Programme P.125: Olympus 101 1st stage LP stright disc for use with Titantium blades by RE Jenkins

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353/10: Olympus Mk.101 LP rotor disc stages 0 & 1. Stresses in rotor discs stages 0 & 1  PA1716/5/11/2/613  5 February 1954

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Contents:
Scheme of drawings used: MS.1709. Performance office data used: PWM.214. Calculations by WJ Cecil

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress clearance record 4353SR/10: Olympus Mk.101 LP compressor with 'O' stage  PA1716/5/11/2/614  11 February 1954

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Contents:
Basic scheme OLS.2010. This note gives general clearance to the above scheme. The main new items are listed in the attached schedule and thereby given specific clearance

Bristol Aeroplane Company. Gas turbines internal memo to Stress Department. Engine Stress investigation 4353SR/10: Olympus Mk.101 with 'O' stage  PA1716/5/11/2/615  23 April 1954

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Contents:
We require to investigate the effect of using the existing 1st stage disc in the 'O' stage position with prsent 1st stage blades extended at the tips and aluminium alloy. RPM = 6400

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/10: Olympus 102 LP compressor rotor 'O' stage disc. Redesigned AL. Alloy disc and new proposed steel disc. Comparison and calculations of offset (rough copy)  PA1716/5/11/2/616  c. 1954

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Contents:
Page 2: CF of fir tree root. Calculations by BPD. Report not dated

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/10:. Olympus 102 LP compressor rotor 'O' stage disc.  PA1716/5/11/2/617  20 April 1956

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Contents:
Rough design of 'O' stage disc for envisaged minimum load and keeping to the same stress graph as for GR.4039 (DRG OLS.3476). Comparison of the weights of the redesigned disc and a new proposed steel disc. Calculations of disc root of offset for redesigned AL.Alloy disc. Calculations by BP Dyas

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/10: Olympus MK.102 LP compressor zero stage disc  PA1716/5/11/2/618  14 March 1956

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Contents:
Design of zero stage disc with modified top profile to same stress level as original zero stage disc. Scheme/drawings used: OLS.3469. Previous calculations referred to: 4353/8; 4353/10. Disc scantlings on MS.2335 (small). Calculations by AH

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress clearance record 4353SR/11: Olympus 103 zero stage LP compressor disc  PA1716/5/11/2/619  27 July 1956

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Contents:
Basic scheme: OLS.3546. WE have examined scheme 03S.3546 showing zero stage compressor disc in BACE.210 carrying AL. alloy 3-lobe root rotor blades to PIM.195 and find it satisfactory for the stresses imposed under ISA SL Static conditions (6500RPM). The stress distribution is shown on MS.2368, a copy of which is enclosed for your information

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/11: Olympus MK.103 LP compressor 'O' stage blade root fixing  PA1716/5/11/2/620  March 1956

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Contents:
The [ ] stresses to the above bead root fixing using the Olympu 6 3 blade broach and the disc design. Performance Office data used: PDM.195 blades. Fir tree fixing stresses summarised 3 April 1957. Calculations by HGP

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4363SR/13: Olympus 104 LP compressor 'O' stage blade fir tree fixing stress summary. Relative strength of blade and fir tree  PA1716/5/11/2/621  3 April 1957

Contents:
Scheme OLS.3995. The calculations compares the strengths of the root section of the blade profile and the blade root neck

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/12: Olympus 104 LP compressor rotor 1st stage (steel). The design of a steel disc for carrying steel blades on a rim lobe root fixing union, the same stress limits as the Olympus 101 1st stage disc  PA1716/5/11/2/622  4 July 1957 - 19 September 1957

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Contents:
Scheme/drawings used: MS.2626. Summarisation MS.2663 attached. Attached MS.2714 Olympus 104 LP compressor 'O' disc (steel). Calculations by BP Dyas

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/12: Olympus 104 LP compressor rotor 'O' stage steel disc. The design of a 'O' stage steel disc  PA1716/5/11/2/623  5 July 1957

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Contents:
Scheme/drawings used: MS.2626, MS.2661. Previous calculations referred to: 4353SR/11 March 1956; and 4363SR/13 (Steel). Page 1: Steel disc and offset. Page 2 DEUCE stresses (MS.2722). Attached. Calculations by BP Dyas.

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/12: Memo from Stress department. Olympus 104 LP compressor rotor 'O' stage steel disc. The design of a 'O' stage steel disc  PA1716/5/11/2/624  7 October 1957

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Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/1: Olympus MK.3HP compressor 5th stage disc. Comparison between steel and Titanium for compressor discs  PA1716/5/11/2/625  11 March 1953

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Contents:
Previous calculations referred to: 4344SR/10. Calculations by JA Taylor

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/1: Memo from Stress Department. Olympus 101 in Avro 698. Production clearance  PA1716/5/11/2/626  9 September 1952

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Contents:
This memo is giving clearance for the Olympus 101 to be fitted to the Avro Vulcan

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 6035SR/58: Memo from Stress Department. Use of S.97 material for Olympus 101 HP compressor discs  PA1716/5/11/2/627  3 March 1953

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Contents:
Formerly 4354SR/1

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 6035SR/58: Memo from Stress Department. S.106 material for Olympus 101 HP compressor discs  PA1716/5/11/2/628  31 March 1953

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Contents:
Formerly 4354SR/1. S.97 rquires replacing with S106 for the Olympus HP compressor discs; the memo goes on the give the technical reasons for this decision

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/2: Olympus HP compressor discs. Stressesing of disc due to CF  PA1716/5/11/2/629  c. 1951

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Contents:
Drawings: OLS.143, 144, 145. Calculations and drawings by: R Farr

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/3: Olympus HP compressor discs & whole assembly  PA1716/5/11/2/630  c. 1952

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Contents:
Gyroscopic deflection of discs considered singly and also considered assembled. Calculations by R Farr

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/4: Olympus rear section compressor. Rear rotor disc  PA1716/5/11/2/631  c. 1953

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Contents:
Stresses in rear rotor discs; 8th stage including labyrinth clearances. File ref: 4344SR/5

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/5: Olympus 103 HP compressor 6th stage rotor disc. Stresses in disc with widened outer rim  PA1716/5/11/2/632  21 September 1956

Contents:
Scheme/drawings used: OLS.3696. Previous calculations referred to: 4364SR/9 by AH & REJ September 1955; 4354SR/5 by DJF 4 February 1953. Calculations by T McDermid

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/5: Olympus 103 HP compressor 8th stage rotor disc. Stresses in disc with widened outer rim  PA1716/5/11/2/633  17 September 1956

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Contents:
Scheme\drawings used: OLS.3704. Previous calulations referred to: 4369SR/9 by AH & REJ September 1955; 4354SR/5 by DJF February 1953. Calculations by T McDermid

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/6: Olympus 101 HP compressor 1st stage disc. Stresses in Titanium disc carrying steel blades  PA1716/5/11/2/634  4 February 1952

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Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/6: Olympus MK.1/2 HP compressor 1st stage rotor disc. Redesign of 1st stage rotor disc in Titanium  PA1716/5/11/2/635  19 October 1953

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Contents:
Schemes/drawings used: B.75385; MS.1659. Previous calculations referred to: 4354SR/6. Calculations by DJ Fortune

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/6: Olympus 101 MK.1/2C HP compressor rotor discs. Design of Titanium discs to cerry Titanium blades for olympus 101 HP compressor rotor  PA1716/5/11/2/636  15 July 1953 - 3 October 1956

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Contents:
Scheme/drawings used: B.77569; MS.1607. Previous calculations referred to: 4354SR/5. Calculations by JA Taylor

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress clearance record 4354SR/5: Olympus 103 HP compressor discs  PA1716/5/11/2/637  3 October 1956

Contents:
Subsidiary schemes OLS.3696, 3704. We have examined the above schemes showing the redesigned 6th and 8th stage compressor rotor discs respectively in S.97 material and find the stresses satisfactory at maximum take-off conditions at 8800 rpm

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/6: Olympus MK.1/2 HP compressor stage 1 rotor discs. Stresses in 1st rotor disc with side load  PA1716/5/11/2/638  27 November 1953

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Contents:
Schemes/drawings used: B.75385; MS 1659. Previous calculations referred to: 4354SR/6; 4344SR/14. Calculations by DJ Cecil

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/7: Olympus MK.1/2 HP compressor lightened rotor discs. Lightened disc profiles for modified Olympus Mk1/2C compressor rotor as on MS.1644  PA1716/5/11/2/639  14 September 1953

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Contents:
Previous calculations referred to: 4354SR/5. Pages 2-24: Stages 1-8 lightened profiles. Pages 25-28: Coning of 1st stage disc. Pages 29-31: Double coning of 7th stage disc. Pages 32-34: Double coning of 8th stage disc. Page 35: Estimate of weight of modified rotor. calculations by AH.

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4354SR/8: B.OL.104 HP compressor 1st stage disc. Stressing of disc at 10,000 rpm  PA1716/5/11/2/640  16 September 1957

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Contents:
Scheme/drawings used: B113935, B.80918. Performance office data used: 4364SR/8, 4364SR/7, 4354SR/[ ]. Calculations by BPD

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation 4353SR/12: Olympus 104 engines and 102 conversions  PA1716/5/11/2/641  28 March 1958

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Contents:
Steel zero and 1st stage compressor blades and discs for these engines are covered by MOD.564, and MoS cover for 50 sets was given in advance of test

Bristol Aeroplane Company. Gas turbines. Stress Department. Engine Stress investigation Summary folder. B.01.6 internal engine conditions (Based on GP.52)  PA1716/5/11/2/642  March 1954

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Contents:
Ref: GP66

Bristol Aeroplane Company. Gas turbines. Performance & Aerodynamics Department. Engine Stress investigation. B.01.6 internal engine conditions (Based on GP.52)  PA1716/5/11/2/643  26 April 1954

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Contents:
Ref: GP71

Bristol Aeroplane Company. Gas turbines. Performance & Aerodynamics Department. Engine Stress investigation. Comparison of stresses in the various blading. The 4th & 5th stages of the Olympus 6 (without offsets)  PA1716/5/11/2/644  c. 1954

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Bristol Aeroplane Company. Gas turbines. Performance & Aerodynamics Department. Engine Stress investigation. LP Compressor rotor blade stress summary 465SR/1. B01.6 stage 1. BACE .301. Scheme S.1211  PA1716/5/11/2/645  12 July 1956

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Contents:
Ref: 465SR/1

Bristol Aeroplane Company. Gas turbines. Stress data sheet. Olympus 6/1 LP & HP compressor shafts. Stress ref: 4346SR/2 & 4346SR/3  PA1716/5/11/2/646  c. 1956

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Contents:
Performance data stress ref 6896/9. Abridged stress summary of HP compressor rotor shaft rear (with drawing). LP compressor rotor tail shaft & rotor drive shaft. Drawing to design scheme 03S.853 Issue 3. Material S106 (Nitrided) Stress summary. Drawing design scheme 03S.1083 HP compressor rotor shaft rear. Material S.106

Bristol Aeroplane Company. Gas turbines. Stress clearance record. Olympus 6/1 HP compressor rotor discs. Stress ref: 4356SR/3  PA1716/5/11/2/647  12 October 1956

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Contents:
Basic scheme 03S.499/6. 03S.876

Bristol Aeroplane Company. Gas turbines. Stress investigation Olympus 6 HP compressor stage 1. STEEL BACE.245  PA1716/5/11/2/648  12 November 1957

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Contents:
Drawing Page 3 MS.2578/1: Dummy blade weigh Type B (1 March 1957) HP compressor. CMS material

Bristol Aeroplane Company. Gas turbines. Stress investigation Olympus 6 G Labyrinth stress summary  PA1716/5/11/2/649  c. 1957

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Contents:
Ref: 46SR/21. Scheme 03S484/3 & 03S.472/1. Outer case BACE.318. Labyrinth Mechanite BACE.S.106

Bristol Aeroplane Company. Gas turbines. Stress investigation Summary of Olympus 6 LP compressor rotor blade stresses with offset blades  PA1716/5/11/2/650  c. 1957

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Contents:
Ref: 4366/SR/5. Material BACE.301

Bristol Aeroplane Company. Gas turbines. Stress investigation. Stress Summary of Olympus 6 LP compressor rotor blades. BACE.301  PA1716/5/11/2/651  c. 1957

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Contents:
Ref: 4366SR/2

Bristol Aeroplane Company. Gas turbines. Stress investigation. Compressor rotor blade stress summary. Engine OL.551. PDM 42 Stages 1, 2, 3 & 5. PDM 318 Stage 4. Al.Alloy BACE 301 (RR.58)  PA1716/5/11/2/652  c. 1956

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Bristol Aeroplane Company. Gas turbines. Stress investigation. Compressor rotor/stator blade stress summary. Olympus 201 LP compressor Stage 1  PA1716/5/11/2/653  14 September 1959

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Contents:
Scheme 03S.2967. PDM. 42 & 114. BACE.245 (FV.FV.458)

Bristol Aeroplane Company. Gas turbines. Stress investigation. Compressor rotor/stator blade stress summary. B0L.6LP compressor LP Stage 1  PA1716/5/11/2/654  27 March 1957

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Contents:
Ref: scheme 03S.1108 BACE.379 (ICI.314A). PDM 42

Bristol Aeroplane Company. Gas turbines. Stress investigation. Drawing & Graph OL.6 5th stage LP Compressor disc  PA1716/5/11/2/655  3 October 1958

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Contents:
Ref: MS.2889. Stress ref 4356SR/4

Bristol Aeroplane Company. Gas turbines. Stress investigation. Drawing & Graph OL.6 4th stage LP Compressor disc  PA1716/5/11/2/656  3 October 1958

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Contents:
MS.2888. Stress ref 4356SR/4

Bristol Aeroplane Company. Gas turbines. Stress investigation. Drawing & Graph OL.6 5th stage LP Compressor disc  PA1716/5/11/2/657  3 October 1958

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Contents:
MS2900. Stress ref 4856/4

Bristol Aeroplane Company. Gas turbines. Stress investigation. Drawing & Graph OL.6 5th stage LP Compressor disc  PA1716/5/11/2/658  3 October 1958

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Contents:
MS2900. Stress ref 4356SR/4

Bristol Aeroplane Company. Gas turbines. Stress investigation. LP Compressor rotor fir tree fixing stress summary. Olympus 200 Scheme 03S.2782  PA1716/5/11/2/659  28 April 1959

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Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 200 LP Compressor rotor blade stress summary  PA1716/5/11/2/660  12 November 1957

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Contents:
Ref: 4366SR12. One page

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 201 LP Compressor rotor blade fir tree fixing stress summary  PA1716/5/11/2/661  October 1959

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Contents:
Ref: 4366SR/5. Scheme 03S.2967

Bristol Aeroplane Company. Gas turbines. Stress investigation. Stress summary Olympus Mk.6 HP Compressor stator blades  PA1716/5/11/2/662  c. 1959

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Contents:
Ref: 4316SR3

Bristol Aeroplane Company. Gas turbines. Stress investigation. Stress summary Olympus Mk.6 LP Compressor stator blades  PA1716/5/11/2/663  c. 1959

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Contents:
Ref: 4316SR2

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 15 LP Compressor stage 1 stator blade Stress summary  PA1716/5/11/2/664  July 1958

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Contents:
Ref: 4326SR/11. Material HYlite 50. BACE.373. 5 Pages covering stages 1 to 5

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 6 HP Compressor stage entry guide stator blade Stress summary  PA1716/5/11/2/665  18 March 1957

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Contents:
Ref: 4316SR/3.Scheme 03S.1641

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus B.0L.6 LP Compressor stator blade Stress summary  PA1716/5/11/2/666  27 March 1957

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Contents:
Ref: 4316SR/2. Scheme 03S.1109

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 551 LP Compressor system. Static load bending moment & shear force diagram (IG)  PA1716/5/11/2/667  4 October 1957

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Contents:
Ref 6896SR/19. Drawn JC

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 551 LP Compressor system. Gyroscopic moment & shear force diagram (1 rad/sec precession)  PA1716/5/11/2/668  4 October 1957

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Contents:
Ref 6896SR/19. Drawn JC

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 200 LP stages 4 & 5 Compressor rotor/blade stress summary  PA1716/5/11/2/669  10 July 1958

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Contents:
Ref 4366SR/55. 2 pages

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 200 LP stages 4 & 5 Compressor rotor blade fir tree stress summary  PA1716/5/11/2/670  17 July 1958

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Contents:
Ref: 4366SR/5. 2 pages

Bristol Aeroplane Company. Gas turbines. Stress investigation. Stress summary. Olympus 551 LP Compressor rotor blade fir tree fixing stresses  PA1716/5/11/2/671  c. 1 March 1957

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Contents:
Ref: 4366SR/5. 1 page

Bristol Aeroplane Company. Gas turbines. Stress invstigation. Olympus 6 LP compressor stage 3 rotor blade fir tree fixing stress summary  PA1716/5/11/2/672  1 March 1957

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Contents:
Ref: 4366SR/5. Scheme 03S.1601

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 6 LP compressor stage 3rotor blade fir tree fixing stress summary  PA1716/5/11/2/673  1 August 1957

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Contents:
Scheme 03S.1923. SR/5

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 6 LP compressor stage 4 rotor blade stress summary  PA1716/5/11/2/674  10 July 1957

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Contents:
Ref: 4366SR/5. Scheme 03S.1246

Bristol Aeroplane Company. Gas turbines. Stress investigation. Olympus 200 LP compressor stage 3 rotor blade stress summary  PA1716/5/11/2/675  January 1959

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Contents:
Ref: 4366SR/15. Scheme 03S.2264

Bristol Aeroplane Company. Gas turbines. Stress investigation Olympus 200 HP compressor stage 2  PA1716/5/11/2/676  28 April 1959

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Bristol Aeroplane Company. Stress investigation Olympus 6 HP  PA1716/5/11/2/677  1950s

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Contents:
Starter, accessory gearbox drive, in Javelin flying test bed

Bristol Aeroplane Company. Stress investigation Olympus 6 HP system helical coupling  PA1716/5/11/2/678  8 December 1955

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Bristol Aeroplane Company. Stress investigation Olympus 6 HP compressor stator blades  PA1716/5/11/2/679  1950s

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Bristol Aeroplane Company. Stress clearance record on Olympus 6/1 and /2  PA1716/5/11/2/680  21 February 1956

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Bristol Aeroplane Company. Stress investigation Olympus 6 LP compressor stage 5  PA1716/5/11/2/681  11 July 1956

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Bristol Aeroplane Company. Schedule of Parts for the S.107  PA1716/5/11/2/682  1950s

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6, Scheme 03S.486/4, /7, and /9  PA1716/5/11/2/683  27 June 1956

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6, Scheme 03S506/4  PA1716/5/11/2/684  21 February 1956

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6/1 and /2, Scheme 03S.602  PA1716/5/11/2/685  22 March 1956

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6/1 and /2, Scheme 03S.584/1  PA1716/5/11/2/686  8 December 1955

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6/1 and /2, Scheme 03S.924  PA1716/5/11/2/687  25 January 1957

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6/1 and /2, Scheme 03S.495/1  PA1716/5/11/2/688  16 December 1954

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6/1, Scheme 03S.853/3 and 03S.1083  PA1716/5/11/2/689  26 May 1956

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Bristol Aeroplane Company. Compressor Rotor Blade Root Fixing Stress Summaries for the Olympus 6/1, 551, 15, 22R, 201 and 21  PA1716/5/11/2/690  1959

11 Items

Contents:
Includes related diagrams

Bristol Aeroplane Company. Stress investigation Olympus 6/1 turbine HP hollow stator 03S.466/1  PA1716/5/11/2/691  1950s

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Bristol Aeroplane Company. Stress investigation Olympus 551, 1st Stage turbine stator blades  PA1716/5/11/2/692  1950s

1 Item

Bristol Aeroplane Company. Stress investigation Olympus 6, Combustion chamber and 1st stage stator assembly, scheme 03S.593/1  PA1716/5/11/2/693  8 March 1956

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Bristol Aeroplane Company. Stress investigation Olympus 6 and 7 turbine interchange, scheme 03S/1620  PA1716/5/11/2/694  1950s

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Bristol Aeroplane Company. Stress investigation Olympus 6, 1st stage turbine casing  PA1716/5/11/2/695  1950s

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Bristol Aeroplane Company. Stress investigation Olympus 6/1 and 6/2 concerning hollow L.P. stator blade  PA1716/5/11/2/696  1950s

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Bristol Aeroplane Company. Stress investigation Olympus 7 HP turbine stator blade  PA1716/5/11/2/697  1950s

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6/1 and /2, Scheme 03S1331  PA1716/5/11/2/698  15 June 1956

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Bristol Aeroplane Company. Stress Data Sheet for Olympus 6/1  PA1716/5/11/2/699  1950s

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Bristol Aeroplane Company. Stress investigation Olympus 6 HP compressor rotor blades  PA1716/5/11/2/700  1950s

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Bristol Aeroplane Company. Stress Clearance Record for the Olympus 6/1 and 2, Scheme 03S.467/2 and 03S.433/1  PA1716/5/11/2/701  8 August 1955

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Bristol Aeroplane Company. Stress investigation Olympus 6, Scheme BLD.272  PA1716/5/11/2/702  2 February 1959

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Bristol Aeroplane Company. Stress investigation Olympus 6, Scheme BLD.272  PA1716/5/11/2/703  1950s

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Bristol Aeroplane Company. Stress investigation Olympus 6, Schemes 03S.467/2, B.201867 and C38.125/9  PA1716/5/11/2/704  1955 - 1957

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Bristol Aeroplane Company. Stress investigation Olympus 301 in Vulcan, turbine/compressor couplings  PA1716/5/11/2/705  1959 - 1960

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Bristol Aeroplane Company. Stress investigation Olympus 301 in Vulcan, turbine/compressor couplings  PA1716/5/11/2/706  21 August 1957

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Bristol Aeroplane Company. Stress investigation Olympus 6 HP turbine shaft  PA1716/5/11/2/707  25 May 1956

1 Item

Bristol Aeroplane Company. Stress investigation Olympus 6 LP turbine sheet, Schemes 03S.258/5 and 03S.279/8  PA1716/5/11/2/708  1950s

1 Item

Bristol Aeroplane Company. Stress Clearance Record concerning Olympus 6/1 and 2 LP and HP turbine shafts  PA1716/5/11/2/709  7 June 1956

1 Item

Bristol Aeroplane Company. Diagrams concerning the Olympus 6 HP and LP compressor system  PA1716/5/11/2/710  19 March 1956

3 Items

Bristol Aeroplane Company. Diagram concerning the Olympus 6/1 HP turbine wheel  PA1716/5/11/2/711  23 August 1957

1 Item

Bristol Aeroplane Company. Diagrams concerning the Olympus 551 compressor system  PA1716/5/11/2/712  31 October 1957

6 Items

Bristol Aeroplane Company. Diagram concerning Olympus 200 LP turbine disc  PA1716/5/11/2/713  July 1962

1 Item

Turbine Programme Note: Engine No.OL.501 (54th Build), Engine Type B.OL.MK.101A, oil flow checks and no.5 bearing investigation  PA1716/5/11/2/714  5 March 1959

1 Item

Turbine Programme Note: Engine No.OL.528 (22nd Build), Engine Type B.OL.MK.101A, high oil inlet temperature investigation  PA1716/5/11/2/715  4 February 1959

1 Item

Correspondence between Stress Department and various individuals concerning Olympus 100 series engines  PA1716/5/11/2/716  1955 - 1959

1 Item

Report on cold forming of fir tree roots by the rolling method  PA1716/5/11/2/717  c. 1950s

2 Items

Contents:
Includes related diagram (in German)

Turbine Development Engineers Department: Report on Olympus Mk.1/2B, 100 and 101 Engines, L.P. Compressor Front End Flanges  PA1716/5/11/2/718  19 November 1953

1 Item

Volume of correspondence between the Stress Office and various individuals concerning Hoffman bearings for Olympus and Proteus  PA1716/5/11/2/719  8 January 1951 - 23 March 1954

24 Items

Volume of correspondence concerning Olympus bearing cages  PA1716/5/11/2/720  30 May 1962 - 11 September 1964

7 Items

Volume of correspondence concerning Olympus 100 Series bearings  PA1716/5/11/2/721  8 January 1960 - 15 December 1960

9 Items

Stress Department Reports: Olympus Casing  PA1716/5/11/2/722  1950s - 1960s

1 Item

Stress Reports: Olympus 6 Compressor Rotor Blades  PA1716/5/11/2/723  1955 - 1957

48 Items

Stress Reports: Olympus 1st HP Turbine Disc  PA1716/5/11/2/724  1950s - 1960s

1 Item

Stress Reports: Olympus Casings  PA1716/5/11/2/725  1950s

15 Items

Research Compressors  PA1716/5/11/2/726  [n.d.]

3 files

Research Compressor 1.A  PA1716/5/11/2/726/1  c.1960s

1 file

Contents:
Records details of air intake, statutory assy, rotor assy, centre section, diffuser, rear bearing and airbox, and strain gauging. Includes item number, part number, drawing number, amendments, scheme number, description, location.

Research Compressor 21B - Planning Department  PA1716/5/11/2/726/2  c.1960s

1 file

Contents:
Records details of air intake, statutory assy, rotor assy, centre section, diffuser, rear bearing and airbox, and strain gauging. Includes item number, part number, drawing number, amendments, scheme number, description, location.

Research Compressor  PA1716/5/11/2/726/3  c.1960s

1 file

Contents:
Records details of air intake, statutory assy, rotor assy, centre section, diffuser, rear bearing and airbox, and strain gauging. Includes item number, part number, drawing number, amendments, scheme number, description, location.

Bristol Aero Engines limited. Bristol Gas Turbines: Olympus 2-300 series aero engines  PA1716/5/11/3  1956 - 1981

Bristol Siddeley Engines Limited: An overhaul facility for the Olympus MK.320 Engine Change unit  PA1716/5/11/3/1  July 1963

1 Item

Contents:
Ref: TS.1486

Bristol Siddeley Engines Limited: Olympus 301 idle rpm at 40,000 feet  PA1716/5/11/3/2  c. 1965

1 Item

Contents:
Undated and unnamed report on the following Vulcans XM.597; XM.598; XM.651; XM.655; XL.389; XM.605; XM.574; XM.594; XM.386; XM.388; XM.646; XM.652; XM.654

Rolls-Royce Limited. Bristol Engine Division: Olympus 200-300 smoke suppression  PA1716/5/11/3/3  11 March 1969

1 Item

Contents:
Ref: MDS224. At the DG.Eng Meeting held at ~Coventry on the 10 October and 18 December 1968 (Minutes reference JLE/IJMI/19686 - dated 19 November 1968 and JLE/IJMI/19867 dated 7 January 1969), the subject of smoke suppression was discussed. Engine bench tests had been tun to establish smoke characteristics with and without additives. It was found that whilst additives reduced smoke omission at 100% LP/RPM to an acceptable test bed standard, the emission level at 70% - 90% LP/RPM was unacceptable by any standard. It was therefore agreed that the company would access the programme necessary to develop a smoke free combustion system

Rolls-Royce Limited. Bristol Engine Division: Bristol Olympus 10,000 20,000 series and 30101 modifications  PA1716/5/11/3/4  1956

1 Item

Contents:
Amendment 18

Rolls-Royce Limited. Bristol Engine Division: 2 drawings of Olympus 20101, 20201 & 20301 compressor casing; 3 drawings of turbine  PA1716/5/11/3/5  c. 1960

1 Item

Contents:
Drawing 7 & 79 compressor casing (rear) also B59432 bracket. Drawing 5 combustion chamber outer casing. Drawing 40 turbine (part 2); Drawing 39 sheet 2 turbine (part 1); 39 sheet 1 turbine (part 1)

Bristol Aero Engines Limited: Drawing TP.4087 Olympus 201 turbojet Fuel system diagram  PA1716/5/11/3/6  6 February 1959

1 Item

Bristol Siddeley Flight Development Section: Olympus 301 Vulcan B.Mk.2 XH557 assessment of 'speed-term' AFRC  PA1716/5/11/3/7  19 July 1963

1 Item

Contents:
Initial tests of the speed-term AFRC as a possible long-term alternative to the existing switch-type AFRC were made in April 1962. Handling was generally good, some surging being expeienced in the in board position, but the major criticism was very slow relighting. While these tests were in progress, it became apparent from other sources that the air distribution in the inboard intake was inferior to that of the outboard intake, with consequent loss of engine surge margin, which made the existing switch-type AFRC unsuitable

MoS: Air Publication AP.1902 Cover 2, Section 4, Chapter 1A AL.86: Vulcan flight idling detent; Maximum friction  PA1716/5/11/3/8  September 1972

1 Item

Contents:
The detent mechanism normally operates at an altitude of 15,000 feet, therefore for adjustment and/or test purposes a similar condition must be created on the ground. This obtained by by-passing the altitude switch, which normally governs the solenoid, with an electrical supply from the test switch on the starboard console. When this switch is operated, the solenoid is energised and retracts

Olympus 300 flame-outs. Rolls-Royce Aero Division Ansty: Olympus 301. Minutes of meeting to discuss flame-out problems held at Parkside  PA1716/5/11/3/9  22 July 1980

1 Item

Contents:
The meeting was held to discuss flame-outs on the Mark 301 engine in service. The problem has been around for many years intermittently but the rate has risen steadily recently with nine incidents so far this year, which is the highest on record. A graph tabled by the Service Department illustrated this trend and the purpose of the meeting was to review evidence and decide what action should be taken to overcome the problem

Olympus 300 flame-outs: RAF Headquarters No.1 Group Bawtry Doncaster Yorkshire. Vulcan 300 series engine flame-outs - advice to aircrew  PA1716/5/11/3/10  21 August 1980

2 Items

Contents:
Ref: 1G/462/2/Air. The recent increase in Vulcan 300 series engine flame-outs has given some cause for concern. The purpose of this letter is to give guidance to aircrew on the actions to be taken in the event of such an occurance. Includes related pilot's report

Olympus 300 flame-outs: Olympus 301. Advice on what to do in the event of a surge and flame-out in normal flight conditions  PA1716/5/11/3/11  11 August 1980

1 Item

Contents:
This is an unsigned hand-written report on the on-going Olympus surge and flame-out problem and how to spot problems before flame-out occurs

Olympus 300 flame-outs: Olympus 301. Engine 900014 its history from 2 November 1962 to 11 June 1980  PA1716/5/11/3/12  27 August 1980

1 Item

Contents:
Olympus 301 900014 in Vulcan XM594 from 10 April 1963 to 5 November 1964. Vulcan XM607 from 19 November 1964 to 8 January 1965. Vulcan XL685 from 3 February 1965 to 27 October 1965. Vulcan XL391 from 11 March 1965 to 26 November 1968. Vulcan XM656/1 from 18 December 1968 to 18 December 1969. Vulcan XJ784/1 from 13 March 1970 to 2 January 1971. Vulcan XM597/4 from 2 February 1971 to 2 November 1972. Vulcan XM603/3 from 13 November 1972 to 11 July 1975. Vulcan XM574/4 from 27 July 1975 to 24 June 1976. Vulcan XM650/4 from 28 July 1976 to 7 march 1977. Vulcan XL388/2 from 16 March 1977 to 29 March 1979. Vulcan XM652/4 from 12 September 1979 to 21 May 1980. Vulcan XM597/3 from 21 May 1980 to 11 June 1980. Attached: Graph Olympus 301 Flight idle speeds at 40,000 feet showing engine flame-outs and Vulcans involved

Olympus 301 flame-outs: Rolls-Royce Memo. Visit to RAF Waddington re. Olympus 301  PA1716/5/11/3/13  29 July 1980 - 1 August 1980

2 Items

Contents:
M Law and GD Andrews visited RAF Waddington on 30 July 1980in order to get a feel for the Station feelings about Olympus 301 flame-out problem. Aircraft XL389 had suffered a double flame-out on 29 July whilst investigating the idling rpm at 40,000 ft, as we had requested through HQSTC. This aircraft had diverted to Leuchars and had not tried to relight

Olympus 301 flame-outs: Vulcan B.Mk.2 XL389  PA1716/5/11/3/14  1965 - 1980

Olympus 301 flame-outs: Bristol Siddeley. Olympus 301 Vulcan B.Mk.2 XL389 relighting with improved combustion chambers to MOD.1508  PA1716/5/11/3/14/1  October 1966

1 Item

Contents:
A set of combustion chambers to MOD.1508 was subjected to Service trials in Vulcan XH557

Olympus 301 flame-outs: Bristol Siddeley Flight Test Department. Olympus 301 in Vulcan B.Mk.2 XL389 relighting with Olympus Modification 1508 flight test schedule  PA1716/5/11/3/14/2  16 November 1965

1 Item

Contents:
Appendix 1

Olympus 301 flame-outs: Rolls-Royce Memo. Olympus 301 relighting data  PA1716/5/11/3/14/3  12 August 1980

1 Item

Contents:
Ref: E/GDA/25562. The attached report covers Olympus 301 relighting with combustion chamber MOD.1508, which was a cascade type chamber with an elongated connector

Bristol Siddeley: Olympus B.O1.21 turbojet engine  PA1716/5/11/3/15  August 1960

1 Item

Contents:
Ref: TC222/2. The Bristol Siddeley B.O1.21 engine is a two-spool turbojet with a maximum rating of 20,000 lbs thrust and a maximum continuous rating of 17,700 lb thrust

Advanced Notification of EMC decisions to Rolls-Royce Coventry  PA1716/5/11/3/16  25 March 1981

1 Item

Contents:
Rolls-Royce: Olympus 1950 (1st Resub) Olympus Mk.202 & 301 engines: Hydraulic pump bevel gear housing assembly. Viper 3973(0) Viper engines: Mk.102, 201, 204, 301.Omnibus modifications, covering minor changes. Viper 3974 Viper Mk.102, 201, 202, 301.Exhaust cone.

RAF Air diagram 8040: Olympus Mk.301 ECU working cycle conditions and air system  PA1716/5/11/3/17  January 1965

1 Item

Contents:
DN90449. Air Publication. AP.783A. Drawing

Bristol Siddeley: Olympus 320 TSR.2 engine & reheat unit flight specification. MoA Contract Ref.KG/M/090/CB(a) Issue 14  PA1716/5/11/3/18  4 January 1965

1 Item

Contents:
Development A Department. Development history Volume 2. Section 2: Olympus 22R to functional 320 conversion specification. Section 3: Fuel system specification. Section 4: Schemes cleared since Issue 1 of Conversion specification. Section 5: Development features required for 150-hour development type test (fighter) schedule. Engine 22213 June 1965 Build. Section 6: List of additionalschemes since the re-issue of OL.320 flight specification to Issue 14. Section 7: Olympus 320X master flight clearance note. Section 8: Olympus 320 master flight clearance note. Section 9: Mechanical condition report on Olympus 320 engine 2209 Build 4. Section 10: Development plan 11/11. Section 11: Specification No.D.Eng.RD.2437. Issue 4. Section 12: BSE Mk.320 supplement to D.Eng.RD.2437 (TRM.44).

Bristol Siddeley Engines Limited: Olympus MK.320 TSR.2 final technical report and development contracts  PA1716/5/11/3/19  21 September 1965

1 Item

Contents:
Volume 1 This report summarises the work casrried out under the following MoA contracts: KG/M/046 KG/M/0112 KG/M/0113 KG/M/0152 KG/M/191 KG/M/189. Section 1: 1 General arrangement of Olympus 22R. 2 Arrangement of Olympus 320. 3 Arrangement of reheat jet pipe. Section 2: 1 Mk.320 engine. 2 Mk.320 engine 3/4 front, port side. 3Mk.320 engine OL.22210 Port side (first production engine). 4 Mk.320 engine 3/4 Rear Port side. 5 Mk.320 engine on test bed. 6 Mk.320 engine.

Bristol Aero Engines Limited. Bristol Gas Turbines: Olympus Mk.200 installation data. Mks. 200, 201  PA1716/5/11/3/20  14 July 1958

1 Item

Contents:
Engines T.2460 issue 3, T.2462A. A jet propulsion engine employing compound axial compressors individually driven by separate single-stage turbines in conjunction with an annular combustion chamber with separate flame tubes

Jets come down to earth: RB 211 unit efficiency allows mid merit prospect  PA1716/5/11/3/21  1973 - 1981

1 Item

Rolls-Royce Ltd and the RB 211 Aero-engine - presented to Parliament by the Secretary of State for Trade and Industry  PA1716/5/11/3/22  1972

1 Item

The aero deprived gas generator as a prime mover for Gas and Oil Transmission, by H.J. Prince  PA1716/5/11/3/23  c. 1970s

1 Item

Presentation Summary: Commercial aero engine developments  PA1716/5/11/3/24  April 1982

1 Item

Brochure: RB.211 in Lockheed Tristar, Propulsion System Maintainability  PA1716/5/11/3/25  July 1971

1 Item

Customer Training Centre: Course Notes - RB.211  PA1716/5/11/3/26  23 January 1973

1 Item

Brochure: Progress on the RB.211  PA1716/5/11/3/27  1971

1 Item

Customer Training Centre: Course Notes - Rb.211  PA1716/5/11/3/28  1973

1 Item

Brochure: RB.211 in Lockheed Tristar, Propulsion System Maintainability  PA1716/5/11/3/29  August 1980

1 Item

Brochure: RB.211 in Lockheed Tristar, Propulsion System Maintainability  PA1716/5/11/3/30  December 1971

1 Item

Brochure: RB211-524, further improving the product  PA1716/5/11/3/31  September 1984

1 Item

Brochure: RB211-524 for the Lockheed L1011 Tristar  PA1716/5/11/3/32  October 1977

1 Item

Brochure: RB211 - Powerful, clean, quiet...  PA1716/5/11/3/33  July 1972

1 Item

Brochure: RB211  PA1716/5/11/3/34  November 1981

1 Item

Leaflet: A 300B - being built today, in service tomorrow  PA1716/5/11/3/35  c. 1970s

1 Item

Technical Features: Rolls-Royce RB.207/211 three shaft turbofans  PA1716/5/11/3/36  May 1968

1 Item

Bristol Gas Turbines: Olympus 593 Concorde engine  PA1716/5/11/4  1961 - 1979

Bristol Siddeley: Olympus 593/3 for AV Roe Canada Limited. Preliminary Type Specification  PA1716/5/11/4/1  November 1961

1 Item

Contents:
TSC 153. The Olympus Mk.593/3 turbojet engine will comprise a two-spool compressor system consisting of a seven-stage low-pressure compressor and a seven-stage high-pressure compressor, mounted independently on separate co-axial shafts. The high-pressure compressor will be driven by a single-stage turbine and the low-pressure compressor by a two-stage turbine, the two rotating systems being mechanically independent of each other. The combustion chamber will be of annular type with separate flame tubes. Engine performance: Take-off (15 minute limit with out bleed) 29,000 lbs. Maximum continuous (unrestricted) 27,650 lbs.

Bristol Siddeley/SNECMA: Olympus 593 Preliminary data  PA1716/5/11/4/2  February 1964

1 Item

Contents:
PS 185. This brochure gives data for the current design standard of the Olympus 593 supersonic civil transport engine, and supercedes all earlier brochures for the Olympus 593, including PS 181. Sufficient information is included in this brochure to enable preliminary aircraft design studies to be made. Examples are included to illustrate the use of the performance curves

Bristol Siddeley/SNECMA: Olympus 593 Suppliers conference  PA1716/5/11/4/3  10 October 1966 - 11 October 1966

1 Item

Contents:
BSS 44. Held at Bristol Siddeley Filton Bristol 10 & 11 October 1966

Rolls-Royce/SNECMA: Maintenance of the Olympus 593  PA1716/5/11/4/4  March 1972

1 Item

Contents:
BSN 66/2. Content Section 1: Prototype experience. Section 2 Scheduled maintenance. Section 3 Maintenance features. Section 4 Engine health monitoring. Section 5 Repair and overhaul. Section 6 Maintenance planning

Rolls-Royce/SNECMA: Olympus 593 for the Concorde  PA1716/5/11/4/5  July 1966

1 Item

Contents:
BSS 26E. Bristol Siddeley was formed in 1959 by the merger of Bristol Siddeley Aero Engines and Armstrong Siddeley Motors. It was further strengthened in 1961 when it acquired the de Havilland and Blackburn Engine companies

Rolls-Royce/SNECMA: Olympus 593 for the Concorde. Minutes of the 11th Propulsion review held at Bristol 24 - 25 November 1976  PA1716/5/11/4/6  24 November 1976 - 25 November 1976

1 Item

Rolls-Royce/SNECMA: Olympus 593 for the Concorde aircraft. Status report for propulsion unit review meeting No.11  PA1716/5/11/4/7  November 1976

1 Item

Contents:
Rolls-Royce (1971) Limited & SNECMA. CESO Service Centre Aero Division, Filton, Bristol. Refer to PA1716/5/11/6 for the minutes of No.11 meeting

Rolls-Royce/SNECMA: Concorde monthly reports. CESO Service Centre  PA1716/5/11/4/8  1977 - 1979

2 Items

Rolls-Royce/SNECMA: Concorde monthly report. CESO Service Centre  PA1716/5/11/4/8/1  June 1977

1 Item

Contents:
Comments: 1 Engine hours for the month were 1668 and total since commencement is now 25,220 hours. 2 Unplanned Engine removals during month. There were 4 unplanned removals. See VI-1-2. of this report. Planned. CBE 161 on 27 June to embody modified air/oil separator to SB79-9 and re-installed. 3 There was one abortive take-off FBVFD on 24 June due to non-illumination of 'GO' light - fault traced to incorrect fuel flow setting.

Rolls-Royce/SNECMA: Concorde monthly report. CESO Service Centre  PA1716/5/11/4/8/2  August 1979

1 Item

Contents:
Comments: 1 Engine hours for the month were 4780. The total since commencement of service being 124,332. 2 Engine removals: There were 11 unplanned and 6 planned (for details see Section V of this report). 3 In-flight shut-down. (For full details see section V) 18/08/79 CBE 066 FBVFD (3) Heavy jolt engine ran down and flamed out. CBE 028 GN94AA (2) TCA light on and gauge confirmation return to JFK. 22/08/79 CBE 063 FBVFA (1) Rapid run-down of all parameters and engine flame-out. return to CDG. 4 Aborted take-off (for details see Section V). 13/08/79 CBX 105 GN94A (4) Low N2 green GO light. 13/08/79 CBE 039 FBTSC (1) Heay surge with EGT rising to 580 deg as throttles opened.

Rolls-Royce (1971) Ltd Industrial & Marine Division: Notes of a meeting to discuss industrial use of the Olympus 593, held at Ansty on 25 January 1974  PA1716/5/11/4/9  29 January 1974

1 Item

Contents:
Olympus Aero. 593 engine types: Some years ago the concorde engine was completely redesigned to give a substantial increase in power, subsequent engines being known as the 593B. Some 31,000 hours of running had been completed by the 593B engine, but in a variety of marks. The current standard known as the Mk.610, introduced a change in fuel system, increase in air throughout of 5% and an annular combustion chamber of the vapourising type. The 610 engine is due to begin production at a rate of three engines per month, beginning April 1974, and about 80 engines are scheduled to be produced. Flying to achieve certification is proceeding and the third production aircraft is due to begin intensive operational trials in October 1974. The fourth production aircraft will join these trials during 1975 and the programme is expected to result in individual engines completing 700 hours of operation. This should clear engines in service for sampling at 1000 hours

Rolls-Royce Limited: Industrial and Marine Division. Olympus 593 Power Turbine Costs  PA1716/5/11/4/10  19 October 1976

1 Item

SNECMA General Statement on Future Development Activity  PA1716/5/11/4/11  c. 1976

1 Item

Rolls-Royce/SNECMA Customer Training Centre: Olympus 593 Mk.610 familiarisation  PA1716/5/11/4/12  28 June 1978

1 Item

Contents:
Olympus Aero. Roll-Royce Aero Engine School

Rolls-Royce/SNECMA Customer Training Centre: Olympus 593 Mk.610 Module change. Training manual  PA1716/5/11/4/13  c. 1979

1 Item

Contents:
Olympus Aero. Rolls-Royce Aero Engine School

Rolls-Royce Olympus 593 Mk.602 Production Aero engines. Uprating of the Mk.601  PA1716/5/11/4/14  c. 1975

Contents:
Undated and unsigned report on the uprating of the Mk.601 Olympus Aero engine

Rolls-Royce Limited: Marine Olympus 593 for Naval ships. Provisional  PA1716/5/11/4/15  November 1973

Contents:
MGT.5068. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. The Olympus 593 Mk.610 Aero engine from which the marine gas generator will be derived, is the power unit for the Anglo-French Concorde supersonic airliner. Based on the considerable experience gained by Rolls-Royce in commercial engine operation, many features have been incorporated which are significat in terms of operating costs and ease of maintenance. These features are of equal significance in the context of marine gas generators

Development Test and Launch Programme Milestone Graphs for Industrial 593  PA1716/5/11/4/16  1970s

18 Items

Concorde publicity material  PA1716/5/11/5  1975 - 1980

Concorde publicity: Concorde's Olympian power. The Olympus story from inception to entry into commercial SST service  PA1716/5/11/5/1  c. 1980

1 Item

Contents:
Olympus Aero. Unknown publication. By Kenneth T Fulton

Concorde publicity: Olympus 593 special. Options into orders. BOAC and Air France sign  PA1716/5/11/5/2  August 1972

1 Item

Contents:
Olympus Aero. Newspaper pull-out (4-page) special Rolls-Royce edition. The full story to date of the Olympus 593 with historical highlights

Concorde publicity: Rolls-Royce/SNECMA Aero-engine data card. Olympus 593 twin-spool supersonic turbojet. Advanced technology for commercial supersonic operation  PA1716/5/11/5/3  c. 1976

1 Item

Contents:
Ref: TJ.325/5 DS3 7053. Rolls-Royce (1971) Limited. Bristol Engine Division, Filton

Concorde publicity: Rolls-Royce/SNECMA 3 data sheets. Olympus 593 Mk.610-14-28  PA1716/5/11/5/4  c. 1978

1 Item

Contents:
BSN 149/4 SSL 8 7059. 1979 Rolls-Royce Limited & SNECMA. Page 2: Graph of engine in operation. Page 3 Drawing of shock waves on engines at supersonic speeds

Concorde publicity: Rolls-Royce/SNECMA (4-page special edition No.6): Flight programme leads to Mach 2  PA1716/5/11/5/5  September 1970

1 Item

Contents:
Page 2: Olympus 593 Mk.602 shortly to replace the Mk.601. Noise reduction and smoke-free operation

Concorde publicity: Rolls-Royce/SNECMA: Illustrations of cutaway of Olympus 593 and Concorde in flight  PA1716/5/11/5/6  c. 1975

1 Item

Olympus gas turbine aero engine school: From Bristol Aero-Engines Limited to Rolls-Royce/SNECMA  PA1716/5/11/6  1950 - 1963

Olympus gas turbine aero engine school: Bristol Aero Engine School. Lecture notes for the Bristol Olympus 101 turbojet  PA1716/5/11/6/1  c. 1950

1 Item

Contents:
Olympus Aero. These notes are for the benefit of people new to aero engines

Olympus gas turbine aero engine school: Bristol Siddeley Engines Limited. Aero Engine School. Lecture notes for the BS Olympus 201 turbojet  PA1716/5/11/6/2  25 September 1959

1 Item

Olympus gas turbine aero engine school: Bristol Siddeley Engines Limited. Aero Engine School. BS Olympus 200 turbine engines  PA1716/5/11/6/3  March 1961

1 Item

Contents:
This book is issued by the Aero Engine School for use by students attending the courses, and it contains sufficient information to supplement the course lectures

Olympus gas turbine aero engine school: Bristol Siddeley Engines Limited. Aero Engine School. BS Olympus 320X (provisional) turbine engines  PA1716/5/11/6/4  August 1963

Contents:
This engine was designed for use in the ill-fated TSR.2 Project

Olympus gas turbine industrial engines  PA1716/5/11/7  1959 - 1981

Bristol Siddeley BS.2101 15 MW Power turbine. Assembly procedure  PA1716/5/11/7/1  June 1961

1 Item

Contents:
Ref: TBD 83. With proposed 15MW (XC3213) installation for Hams Hall

Bristol Siddeley BS.2400 bhp 17.5 MW Power turbine. Technical specification Supplement  PA1716/5/11/7/2  c. 1961

1 Item

Contents:
Ref: Supplement to PA1716/5/11/7/1 for Hams Hall CEGB 17.5 MW generating set

Bristol Siddeley BS.70/80 MW turbo-generator. General description  PA1716/5/11/7/3  October 1963

1 Item

Contents:
Ref: IGT 143. Supercedes IGT92. Features of the 70/80 MW set comprising four Olympus BS.2001 gas generators coupled to Olympus BS.2104/5 power turbine, together with auxiliaries

Bristol Siddeley BS.17.5/20 MW turbo-generator. General description  PA1716/5/11/7/4  February 1964

1 Item

Contents:
Ref: IGT.138. Supercedes IGT.94 The gas turbine driving the ac generator, consists of a Bristol Siddeley Olympus gas generator, and a separate two-stage axial-flow power turbine unit, also of Bristol Siddeley design

Bristol Siddeley BS.35/40 MW turbo-generator. General description  PA1716/5/11/7/5  February 1964

1 Item

Bristol Siddeley: BS.17.5 gas turbo-generating unit. Installed at Central Electricity Generating Board Tilbury 'B' Power station  PA1716/5/11/7/6  October 1965

1 Item

Contents:
Ref: IGT 105. BS.2006 gas turbine, compound axial flow compressors five and seven-stage with two-stage turbines

Bristol Siddeley: Olympus TG.2S turbo-generator. Technical specification  PA1716/5/11/7/7  June 1966

1 Item

Contents:
Ref: IGT 241. Two industrial Olympus gas generators are employed, being connected to a single stage power turbine which drives an ac generator

Bristol Siddeley: Olympus 17.5 MW turbo-generator. General description  PA1716/5/11/7/8  January 1967

1 Item

Contents:
Ref: IGT 278. Supercedes IGT 138. The Olympus gas generator is a straight flow high pressure ratio unit, with a five-stage low pressure compressor and a seven-stage high pressure compressor arranged co-axially

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Specification No.IP01. Issue 1: Specification for Olympus Type 2016 gas generator  PA1716/5/11/7/9  24 May 1967

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The Olympus Type 2016 gas generator is intended for continuous duty operation on gaseous fuels, in conjunction with a customer supplied power turbine. The gas generator is an engine having a 5-stage low-pressure compressor in tandem with a 7-stage high-pressure compressor, each compressor being separately driven by a single-stage turbine via co-axial shafts

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial gas generator. General description  PA1716/5/11/7/10  January 1970

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IGT 286. Issue 2. The Olympus gas generator described in this brochure has been developed from the Olympus turbojet aero engine, well known in military aviation for its reliability and high performance. An advanced development of this engine provides the power for the Anglo-French supersonic airliner Concorde

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: General specification No.10057 for Olympus B rating Industrial gas generator dual-fuel system. Description  PA1716/5/11/7/11  November 1970

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Contents:
Ref: 10057. The 2000 series Olympus is a gas generator having a 5-stage low pressure compressor in tandem with a 7-stage high-pressure compressor, each compressor being driven independently by a single stage turbine via a co-axial shaft

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus B rating 320 Industrial gas generator gas fuel system. General description  PA1716/5/11/7/12  January 1971

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Contents:
Ref: 10058

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Power turbine unit. General description  PA1716/5/11/7/13  January 1970

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Contents:
Ref: IGT 2344. Power turbines similar to the unit described in this brochure are currently employed with Olympus gas generators, as power units driving electrical generators in 17.5 MW sets; the first installation started operating at the CEGB Hams Hall power station in 1962

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Project study for a 70 MW industrial gas turbine  PA1716/5/11/7/14  c. 1965

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Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial engines. Part A mandatory installation requirements  PA1716/5/11/7/15  May 1969

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Contents:
Ref: IGT 332/A. This brochure has ben prepared to assist the purchaser in designing the installation of the Industrial gas generator (2000 series)

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial engines. SK 20M compact. Single package generating set for offshore rigs and platforms  PA1716/5/11/7/16  June 1974

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Contents:
Ref: IGT 5096. The Olympus powered SK 20M compact generating set has been specifically designed as a lightweight package unit. Can be transported by helicopter or rig vessel (weight 2177kg). The Olympus Aero engine (200 series) originally developed in 1953 for the Vulcan V bombers, was first put into service in sea level operation as an industrial power generation engine for the CEGB. These were commissioned in September 1962 for Hams Hall power Station near Birmingham. The Hams Hall Olympus 17.5MW turbo-generating set has operated for over 22,000 hours on gas fuel. This was followed by further orders from CEGB for Industrial Olympus engines and also orders from abroad, the most recent order being for an SK20 packaged generating set sold to Malawi for operation by the Electricity Supply commission (ESCO)

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial engines. Rolls-Royce SK100 generating set with the Olympus 593  PA1716/5/11/7/17  May 1975

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Contents:
Ref: IGT 5136. The Olympus SK100 packaged generating aet, initially designed for a peak power approaching 100 mW, is powered by two Olympus 593 gas generators, each driving three-stage power turbines at either end of an ac generator. In common with lower powered SK40 and SK60 units, the double ended configuration provides flexibility of operation and high efficiency at part load with the gas turbines at one end shut down

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial engines. SK range of packaged generating sets. general description  PA1716/5/11/7/18  January 1975

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Contents:
Ref: IGT 5109. The Roll-Royce SK range of generating sets consists of a number of self-contained packages which are individually transported to site and then assembled to form complete generating sets. The SK range includes both single and double-ended units driven by either the B standard or C standard Olympus and covers the power range from 20MW to MW. Both the Olympus gas generator and the power turbine are basically similar to sets at present in service or on order for power stationed in Great Britain and in countries throughout the world including: Mozambique, Canary Islands, Channel Islands, Holland, Japan, Malawi and Australia

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial engines. Packaged generating sets based on the Industrial 593 (preliminary)  PA1716/5/11/7/19  September 1976

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Contents:
Ref: IGT 5196. The industrial 593 will be world's largest aero derivation, capable, at entry to the market in 1980, of 48.5 MW in a single-ended set, and 97 MW in a double-ended set. The first industrial of this family of engines, based on the 201 series aero engine, entered service with the CEGB in 1962 at Hams Hall. Since that time 222 Industrial Olympus engines have been sold with an aggregate power capability of 4.4 million KW providing 287,000 operating hours, almost all in peak lopping duty

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial engines. SK50 Olympus 593 power turbine feasibility & assembly study  PA1716/5/11/7/20  January 1978

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Contents:
Prepared by the production Planning Department

Rolls-Royce Limited Industrial & Marine Gas Turbine Division Ansty: Olympus Industrial engines. Mahoudiya Power Station for the Egyptian Electricity Authority  PA1716/5/11/7/21  November 1979

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Contents:
Ref: IGT 5346. Backgound: The Egyptian Electricity Authority supply system depends largely on hydro-electic energy (in 1977 66%), and water supply available for driving electric turbines is dependent on seasonal fluctuations in the Nile flow rate. Between January and July this flow is so drastically reduced that it seriously affects the Egyptian Electricity Authority's base load capability. To supplement their capability during this low flow period the Egyptian Electricity Authority have purchased from Rolls-Royce a 200 MW gas turbine driven (4 SK60) generating station. It is envisaged that the machines will operate for up to 4000 hours per year in supplementing the supply between these months. During the rest of the year they will be used to protect the system in the event of an emergency

Rolls-Royce Industrial & Marine Division: Industrial Olympus gas generator  PA1716/5/11/7/22  c. 1962

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Contents:
Ref: IGT 5005. Rolls-Royce (1971) Ltd, 1972. The Olympus gas generators power a single engined generating sets with an output of 17.5 MW at ISAv conditions, and a further development shortly available will allow unts to generate 25 MW ISA. Multiple units with four gas generators are operating, currently giving 40 MW and 80 MW respectively

Rolls-Royce Industrial & Marine Division: drawings of Industrial Olympus gas turbine generator  PA1716/5/11/7/23  c. 1975

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Rolls-Royce Industrial & Marine Division: Cut-away drawing of Industrial Olympus gas turbine generator  PA1716/5/11/7/23/1  c. 1975

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Contents:
Cut-away drawing of 1 17.5 MW generating set; 2 70 MW generating set; 3 English Electric 35 MW generating set

Rolls-Royce Industrial & Marine Division: Drawing of Industrial Olympus gas turbine generator  PA1716/5/11/7/23/2  c. 1975

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Contents:
Detailed drawing of Industrial Olympus types 2006, 2008 and 2020. (A) Showing items which may be removed from an installed engine; & (b) Items can only be removed from an engine that is not installed.

Rolls-Royce Industrial & Marine Division: Drawing of Industrial Olympus SK20 gas turbine generator  PA1716/5/11/7/23/3  c. 1975

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Contents:
Ref: T01 HM 012. A showing items which can be removed from an installed engine; & B Items can only be removed from an engine that is not installed. Position of assemblies that may be worked upon

Rolls-Royce Industrial & Marine Division: Drawing Industrial Olympus 2008 turbine assembly removal  PA1716/5/11/7/23/4  c. 1975

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Contents:
Three drawings of engine; 1 complete engine; 2 (top right 8) Inner exhaust cone, 7 Remove oil tube. 3 Casing for turbine shaft

Rolls-Royce Industrial & Marine Division: General Arrangement drawing (in colour) of gas flow Industrial Olympus gas generator  PA1716/5/11/7/23/5  c. 1975

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Rolls-Royce Industrial & Marine Division: Cut-away drawing of Industrial Olympus gas generator  PA1716/5/11/7/23/6  c. 1975

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Contents:
Cut-away drawing (in colour)

Bristol Siddeley: Drawing of Industrial & Marine Olympus gas generator  PA1716/5/11/7/23/7  c. 1960

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Contents:
Cut-away drawing (in colour)

Bristol Siddeley: 3 drawings of Olympus gas generator air system diagram in colour  PA1716/5/11/7/23/8  c. 1960

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Contents:
Ref: Fig.3.81. 3.137/138

Bristol Siddeley: Drawing of Olympus gas generator on display stand  PA1716/5/11/7/23/9  c. 1960

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Rolls-Royce Industrial & Marine Division: Arrangement drawing of Industrial Olympus stage 2 power unit  PA1716/5/11/7/23/10  12 March 1975

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Contents:
Arrangement drawing IPS.13633A

Rolls-Royce Industrial & Marine Division: Cut-away drawing of Skid mounted Olympus gas turbine generator  PA1716/5/11/7/23/11  c. 1975

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Contents:
Coloured engineering cut-away drawing

Bristol Siddeley Engines Limited Marine & Industrial Gas Turbine Department: Increased size Olympus power turbine  PA1716/5/11/7/24  28 December 1962

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Contents:
Industrial Olympus. Ref: TGD/FRS/JCG/623/634. Further to the note of 5 November 1962, please find attached the thermodynamics for the turbine running at the 20 MW condition

Bristol Siddeley Engines Ltd Aerodynamics Ansty: 15 megawatt Olympus turbiner exhaust system  PA1716/5/11/7/25  28 June 1960

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Contents:
Industrial Olympus. Report on an estimation of the overall loss coefficient for the diffuser (Fig.1) was required

Bristol Siddeley Engines Limited: 2 Drawings of hp & lp compressor casing removal of topsection for inspection of rotor blades  PA1716/5/11/7/26  c. 1965

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Bristol Siddeley Engines Limited. IMD GT Department. Industrial Olympus: 2 70/80 megawatt gas turbine generating sets Ryehouse Hoddesdon Hertfordshire  PA1716/5/11/7/27  August 1964

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Contents:
Test schedule OTS.46. This report covers all the tests to be carried out, on all parts of the system, prior to commissioning

Rolls-Royce: Olympus Industrial engines. Series 2017-B gas generator  PA1716/5/11/7/28  March 1970

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Contents:
PSR.183. Issue 1. IGT.3947. The Rolls-Royce Series 2017 Industrial Olympus B gas generator, has improved performance and reliability compared with the earlier Series 2013 Olympus A; it can run on distillate fuel and natural gas. The operation of an industrial gas generator is intrinsically linked with the free power turbine it is driving; in particular the gas generator compressor working conditions are affected by the effective free power turbine swallowing capacity when referred to the Olympus exhaust (ie allowing for any ducting leakage and pressure losses), which directly affects the power output available. To achieve the rated output therefore, it is essential that a gas generator be operated in conjunction with a free power turbine of specific capacity at the design conditions

Rolls-Royce IMD GT Division: Olympus Industrial gas generator. General description  PA1716/5/11/7/29  January 1970

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Contents:
IGT.286. Issue 2. This is a straight flow high-pressure ratio gas generator with a five-stage low-pressure compressor and seven-stage high pressure compressor arranged in tandem, each driven independently by its own turbine through co-axial shafts

Bristol Siddeley: Project Study. Proposal for an experimental vapour turbine  PA1716/5/11/7/30  September 1966

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Contents:
IGT.268. Bristol Siddeley Engines Limited Ansty. Performance and installation studies have ben carried out on a generating plant working on a binary cycle.Calculations suggest that a plant combining the Olympus gas turbine with a vapour turbine can offer substantial improvement in effeciency with no appreciable increase in the installation cost per unit power generated. The combined plan, which generates 100 MW power, is described in a separate brochure. In order to demonstrate that the expected performance can be obtained, it is proposed to build an experimental vapour turbine and test it in conjunction with the Olympus 17.5 MW set possibly at Hams Hall. These tests will also povide confirmatory design data for the proposed 100 MW set. This brochure describes the experimental set and the modifications that are necessary to the existing installation at Hams Hall to incorporate the vapour turbine

Rolls-Royce: MoD (AS) Pump research review of progress and proposals for work in period up to March 1972  PA1716/5/11/7/31  August 1971

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Contents:
Contract No.K47B/84/CB.47(b). Rolls-Royce Industrial and Marine Division. Backing pump work

Rolls-Royce: Rolls-Royce paper on compact gas turbines for electrical generation  PA1716/5/11/7/32  January 1980

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Contents:
IGT.5348 Rolls-Royce Industrial and Marine Division

Rolls-Royce: Fuels flexibility Rolls-Royce and alternative fuels  PA1716/5/11/7/33  June 1980

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Contents:
IGT.5367. Rolls-Royce Industrial and Marine Division. The two most conventional gas turbine fuels which the majority of Rolls-Royce units throughout the world operate are natural gas and No.2 gas oil which is a diesel distillate

Rolls-Royce Industrial & Marine Division: Olympus 3 Stage Power Turbine Report  PA1716/5/11/7/34  18 December 1959

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Bristol Siddeley Engines Ltd: Report on Increased Size Olympus Power Turbine  PA1716/5/11/7/35  5 November 1962

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Bristol Siddeley Engines Ltd: Tender for 70/80 MW gas turbine installation at Tilbury B Power Station for CEGB Southern Project Group  PA1716/5/11/7/36  8 December 1961

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Contents:
Attached as part of the tender document: Acceptance letter from the Central Electricity Generating Board dated 27 February 1962

Bristol Siddeley: Project Study. Proposal for an experimental 17.5 MW vapour turbine  PA1716/5/11/7/37  1966

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Contents:
Project No.1007. Bristol Siddeley Engines Limited Ansty. Summary (par 4): CEGB have expressed interest in an experimental plan and the brochure describes, in outline, an experimental 17.5 MW set at Hams Hall. The turbine would be a half-scale model of a 30 MW machine forseen as the vapour turbiner of a 100 MW binary plant

Rolls-Royce Industrial Gas Turbines for Power Generation  PA1716/5/11/7/38  September 1981

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Rolls-Royce Combined Cycle Project in conjunction with Stork B.V. for The Hague, Holland  PA1716/5/11/7/39  July 1980

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Industrial Engine: Support Document, IGT 5002/5  PA1716/5/11/7/40  April 1973

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Rolls-Royce: Alternative Methods of Crude Fuel Treatment for Rolls-Royce Gas Turbines, IGT 5349  PA1716/5/11/7/41  c. 1980s

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Rolls-Royce: Summary of low Btu fuel burning investigations with Rolls-Royce industrial gas generators  PA1716/5/11/7/42  March 1981

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Rolls-Royce Industrial and Marine Division: Minutes of a meeting to discuss industrial use of Olympus 593, held on 5 October 1972  PA1716/5/11/7/43  9 October 1972

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Bristol Siddeley Engines Ltd: Performance tests of the 0.55 scale rig version of the Olympus 593B HP turbine  PA1716/5/11/7/44  8 February 1966

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Bristol Siddeley Engines Ltd: Performance Tests of a 0.55 scale rig version of the Olympus 593D HP turbine  PA1716/5/11/7/45  8 December 1964

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Rolls Royce: The application of gas-turbines to reactor systems  PA1716/5/11/7/46  c. 1960s

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Technical Specification: Bristol Siddeley, Industrial Olympus Power Unit  PA1716/5/11/7/47  c. 1960s

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Press cuttings: 15/18 MW Gas Turbo-Generator Hams Hall Press Day  PA1716/5/11/7/48  19 October 1962

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Olympus 593: Aspects of Smoke and Pollution  PA1716/5/11/7/49  June 1971

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A Guide to Industrial Applications for Rolls-Royce Products  PA1716/5/11/7/50  1960s - 1970s

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Olympus 593 Blade Frequency Diagrams  PA1716/5/11/7/51  1960s - 1970s

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Photoelastic Analysis of Olympus 593 HP Turbine Blade, Report No. 35-5  PA1716/5/11/7/52  April 1978

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Customer Training Centre: Modular Change, Industrial RB211 Gas Generator  PA1716/5/11/7/53  January 1983

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Customer Training Centre: Course Notes, Industrial RB211 Gas Generator  PA1716/5/11/7/54  c. 1981

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Customer Training Centre: Course Notes, Marine and Industrial Olympus  PA1716/5/11/7/55  1 September 1976

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Module Change: ;Industrial RB211  PA1716/5/11/7/56  June 1980

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Uprating of the Industrial RB211  PA1716/5/11/7/57  May 1982

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General Description: The Industrial RB211  PA1716/5/11/7/58  July 1980

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General Description: The Rolls-Royce Industrial RB211 Gas Generator  PA1716/5/11/7/59  1973

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General Description: The Industrial RB 211  PA1716/5/11/7/60  1976

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Information: Offshore Role for Rolls-Royce RB 211  PA1716/5/11/7/61  26 August 1980

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The Engineer: Industrial turbines spin out the fuel  PA1716/5/11/7/62  21 March 1974

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Brochure: RB 211 Industrial Gas Turbine  PA1716/5/11/7/63  1981

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Brochure: Industrial RB211 Gas Generator  PA1716/5/11/7/64  December 1972

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Brochure: Industrial RB211 Engine Management  PA1716/5/11/7/65  April 1990

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Brochure: Industrial RB211 Modular Construction  PA1716/5/11/7/66  September 1973

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Brochure: Industrial RB211 Condition Monitoring  PA1716/5/11/7/67  June 1973

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File of publicity relating to Industrial RB211  PA1716/5/11/7/68  1960s - 1970s

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File of photographs relating to industrial, marine and aero engines  PA1716/5/11/7/69  c. 1960s

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General Specification No. 10059 for Olympus 'B' Rating Industrial Gas Generator Liquid Fuel System  PA1716/5/11/7/70  November 1970

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Contents:
Report.

RB211 .535 E4 General Arrangement Drawing  PA1716/5/11/7/71  1985

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Contents:
Large plan.

RB211-22B general Arrangement Drawing  PA1716/5/11/7/72  1977

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Contents:
Large plan.

Skid Package Set SK20 Phased Site Erection Sequence  PA1716/5/11/7/73  c.1977

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Contents:
Report by Rolls-Royce Limited Industrial and Marine Division

Olympus Industrial gas turbine engines. Hams Hall & later power stations  PA1716/5/11/8  1962 - 1976

Bristol Siddeley 15/20 MW Olympus Industrial gas turbine generating plant installed at Hams Hall Generating station for CEGB. Maintenance manual  PA1716/5/11/8/1  June 1963

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Contents:
Ref: IGT.33. This manual contains the information for operating and maintaining in a serviceable condition the Bristol Siddeley 15 MW Olympus turbo-generator set, as installed at CEGB Hams Hall. Part 1: comprises information on the description operation and servicing of the gas generator and power turbine. Part 2: deals with the description and servicing of the ac generator. Part 3: comprises general information and servicing instructions on the electical control gear

Bristol Siddeley 17.5/20 MW Olympus Industrial turbo-generator plant installed at Hams Hall for CEGB  PA1716/5/11/8/2  March 1965

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Contents:
Ref: IGT 204/3/65 supercedes IGT 74/1/63. Four-page folding leaflet

Pub: Bristol Siddeley 17.5/20 megawatt Olympus Industrial turbo-generator installed at Hams Hall for CEGB  PA1716/5/11/8/3  January 1963

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Contents:
Ref: IGT 74/1/63. Four-page fold-out publicity leaflet

Newspaper cuttings re commissioning power station  PA1716/5/11/8/4  1962 - 1976

Newspaper cutting Steam Engineer: Hams Hall gas turbine. Details of a prototype 15MW unit installed for peak load and emergency duty  PA1716/5/11/8/4/1  December 1962

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Contents:
Two page article on the Bristol Siddeley Olympus gas generators

Newspaper cutting Townsville Daily Bulletin: To commission power station  PA1716/5/11/8/4/2  24 June 1976

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Contents:
The Minister for Mines and Energy, Mr RE Camm, next Saturday, will officially commission Stage 1 of North Queensland's first gas-turbine power station in Mackay. Mr MacKay said that as the result of the new plant, electricity consumers throughout the entire NEA supply system from north of Cairns to south of Mackay, would obtain the benefit of increased power supplies. He said this stemmed from the gas turbine station's capability of generating power for the supply system within seconds of start-up. The manufacturer and installation of the complex plant, based around an industrial version of the Olympus gas turbine ued in the supsonic Concorde jetliner, has been performed under contract by the Industrial & Marine Division of Rolls-Royce (1971) Ltd. Inustrial Olympus 593

Newspaper cutting Mackay Mercury: At the commissioning of a power station  PA1716/5/11/8/4/3  28 June 1976

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Contents:
Photo of Minister of Mines and Energy; Mr FA MacKay Director of marketing Rolls-Royce Australia Ply Ltd.

Newspaper cutting Mackay Mercury: Power Plant's first stage commissioned  PA1716/5/11/8/4/4  28 June 1976

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Contents:
The first stage of the Northern Electric Authority's new gas turbine plant in Hurne Street, Mackay, was officially commissioned om Saturday. The NEA gas turbine power station in Mackay attracted international attention because it was the largest of the new Rolls-Royce generators yet sold anywhere in the world. The first stage of the the gas turbine plant will boost generating capacity available for the whole of Queensland by 17,000 kilowatts. The plant will extend in 12 months by the addition of a second jet engine which will increase its generating capacity from 17,000 to 34,000 kilowatts. Olympus 593 industrial engines

Newspaper cutting Cairns post: Rolls' Power Station  PA1716/5/11/8/4/5  21 July 1976

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Contents:
The station which cost $5 million at Mackay has been designed to produce 34 MW of power by means of two giant Rolls-Royce 17 MW Olympus 593 industrial gas turbines

Letter from The Northern Electric Authority of Queensland to Rolls Royce Press Office regarding prints and newspaper articles concerning the gas turbine commissioning  PA1716/5/11/8/4/6  2 August 1976

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Bristol Siddeley: Press release No246. Industrial Olympus New gas turbo-generator commissioned in the Midlands CEGB's 15/18 MW stand-by set is first in Europe  PA1716/5/11/8/5  1962

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Contents:
Book of press releases and articles from newspapers and magazines re. the Olympus Industrial gas turbine generator

Rolls-Royce Industrial & Marine Division Ansty: Conversion of Hams Hall Power Station to gaseous fuel  PA1716/5/11/8/6  24 August 1967

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Contents:
This bochure describes the work necessary for the conversion of the existing Hams Hall gas turbine installation from liquid fuel to gas fuel burning

File of photographs of Hams Hall industrial generator sets  PA1716/5/11/8/7  c. 1960s

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Olympus Marine gas turbine engines  PA1716/5/11/9  [n.d.]

Bristol Siddeley Engines Limited: Marine Olympus. General description  PA1716/5/11/9/1  August 1961

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Contents:
Ref: TBD.88. The lightweight marine power unit, consisting of an Olympus gas generator and lightweight power turbine, has a background of extensive development and operation unusual in marine engines. The gas generator is derived from the Olympus aero engine which has been in service with the RAF since 1956. and has gained a reputation for reliability and good handling qualities. The modifications necessary for marine use do not affect the basic design, being mainly the removal of unnecessary aero equipment and changes in materials to resist corrosion by sea water

Bristol Siddeley Engines Limited: Olympus marine gas generator Type BS.2002 for brown Boveri Power Turbine. Operation & maintenance manual. Abridged  PA1716/5/11/9/1/1  September 1962

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Bristol Siddeley Engines Limited: Marine Olympus. Special rating. General description  PA1716/5/11/9/2  December 1963

Contents:
Ref: MGT.78. This brochure supercedes MGT.42. Attached Marine Olympus Technical brochure MGT.78 Amendment List No.1 June 1965. The Olympus gas generator is a straight-flow, high pressure ratio unit with a five-stage low pressure compressor, and a seven-stage high pressure compressor, each driven by its own single-stage turbine

Bristol Siddeley Engines Limited: Marine Olympus. (Special rating). Technical brochure MGT.78. Amendment List No.1  PA1716/5/11/9/2/1  June 1965

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Contents:
Ref: MGT.78

Bristol Siddeley Engines Limted: Marine Olympus. Normal rating. General description  PA1716/5/11/9/3  June 1965

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Contents:
Ref: MGT.118. The marine Olympus gas turbine Type TM.1 consists of a gas generator unit, and a separate single-stage axial-flow power turbine

Bristol Siddeley Engines Limited: Marine Olympus TM.2 (24,000 bhp). General description  PA1716/5/11/9/4  August 1966

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Contents:
Ref:MGT.150. The marine Olympus gas turbine Type TM.2 consists of a gas generator unit, and a separate single-stage axial-flow power turbine. The two units are connected solely by a bellows joint, consequently attachment or removal of the gas generator is a simple operation

Bristol Siddeley Engines Limted: Marine Olympus Gas generator 2017. General description  PA1716/5/11/9/5  May 1968

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Contents:
Ref: MGT.240. This brochure presents the necessary technical information for the matching of the marine Olympus gas generator with a suitable power turbine unit, and to give a general description of gas generator construction, installation, control and servicing

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus Gas Turbine Type TM.3B  PA1716/5/11/9/6  1968 - 1974

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus Gas Turbine Type TM.3B. General description  PA1716/5/11/9/6/1  January 1970

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Contents:
Ref: MGT.187. Amendment list No.3

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus Gas Turbine Type TM.3B. General description  PA1716/5/11/9/6/2  July 1971

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Contents:
Ref: MGT.187. Amendment list No.4

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus Gas Turbine Type TM.3B. Machinery Supply Proposal  PA1716/5/11/9/6/3  June 1974

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Contents:
Ref: MGT.5004. Amendment No.AL.3

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus Gas Turbine Type TM.3B. General description  PA1716/5/11/9/6/4  February 1968

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Contents:
Ref: MGT.187. With Amendment List No.3 - January 1970; Amendment List no.4 -July 1971; & Amendment No.AL3 - June 1974

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus TM.3B Machinery supply proposal  PA1716/5/11/9/7  1971 - 1976

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus TM.3 Machinery supply proposal  PA1716/5/11/9/7/1  September 1975

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Contents:
Ref: MGT.5004. Revision 4

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus TM.3B Machinery supply proposal. General description  PA1716/5/11/9/7/2  March 1976

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Contents:
Ref: MGT.5004. Revision 5

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Marine Olympus TM.3B Machinery supply proposal. General description  PA1716/5/11/9/7/3  October 1971

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Contents:
Ref: MGT.5004. Development of the marine Olympus started in 1962, and the engine was installed in the first of the Finnish gunboats in 1967, using a brown Boverei power turbine. In 1968 the Olympus went to sea in HMS Exmouth using a Rolls-Royce power turbine. The gas generator used in these applications was the 'A' rated TM.1 Unit, with uncooled turbine nozzles and blades, developing 24,000 bhp at 59degF (15C) with nominal entry temperature of 1150degK. This 'A' rated gas generator is also being installed inHMS Bristol and in six frigates for Malaysia, Iran and Libya

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. For shore trials of the Marine Olympus TM.3B module in support of the Type 42  PA1716/5/11/9/8  September 1972

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Contents:
Ref: DCP 008/St.3/5

Rolls-Royce Industrial & Marine Gas Turbine Division Ansty. Interim report on shore trials of the prototype Marine Olympus TM.1 power unit  PA1716/5/11/9/9  13 October 1967

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Contents:
Ref: MoD(N) Contract N/CP 95/570 65/64/7C102/KA 1778. Rolls-Royce Service Order 431029. This report gives aninterim statement of progress on the TM.1 development at Ansty up to the completion of 300 hours running time against the above contract

The Institute of Marine Engineers Transactions. The Bristol Siddeley Olympus Marine Gas Turbine  PA1716/5/11/9/10  May 1967

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Contents:
Reprinted from the Institute of Marine Engineers. May 1967 Vol.79 No.5

Rolls-Royce (1971) Limited Marine & Industrial Division: Marine Olympus TM3 Module  PA1716/5/11/9/11  1972 - 1979

Rolls-Royce (1971) Limited Marine & Industrial Division: Marine Olympus TM3 Module  PA1716/5/11/9/11/1  April 1979

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Contents:
Ref: MGT 5311-4/79

Rolls-Royce (1971) Limited Marine & Industrial Division: Marine Olympus TM3 Module  PA1716/5/11/9/11/2  c. 1972

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Contents:
Ref: MGT 5003. Type 42 destroyer; Vosper-Thorneycraft Mk.10 frigates; Yarrow Frigate RAHMAT; Vosper Mk.5 Frigate

Rolls-Royce Limited Marine & Industrial Division: Olympus Marine power  PA1716/5/11/9/12  September 1969

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Contents:
Ref: MGT 1631. Fast patrol boats; hydrofoils; hovercraft; destroyers, frigates and gunboats

Rolls-Royce Limited Marine & Industrial Division: Industrial and marine calendar 1980  PA1716/5/11/9/13  1980

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Bristol Siddeley Engines Limited. Feasibility study: Marine Olympus radial power turbine  PA1716/5/11/9/14  May 1964

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Contents:
Manual G.95. This report presents the results of a feasibility study of reversible propulsion turbines associated with Olympus gas generators authorised under Admiralty Contract CP.8(1)53559/63/M.592/DRD.5. Each propulsion unit, of radial inward flow type, is required to accept half the gas from an Olympus gas generator and to produce an output of 9,000shp ahead and 3,000shp astern

Rolls-Royce Limited. Feasibilty study: Gas turbine propulsion module with vertically mounted Marine Olympus TM.3(b).a.V  PA1716/5/11/9/15  22 December 1967

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Contents:
Ref: VAW/RMJ/616/2629. For the purpose of this study document the engine will be referred to as TM.3.a.V. Where TM.3 refers to power turbine design, (b) is the power rating of the Olympus 'a' (or 'c') denotes the direction of rotation of the output coupling, and V denotes vertical mounting of the Olympus gas generator. The MoD(N) statement of requirements for the feasibility study is included in section 2

Bristol Siddeley Limited, Ansty: Design specification for the BS.01.2202 gas turbine engine  PA1716/5/11/9/16  August 1961 - December 1962

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Contents:
The engine consists of a version of the Olympus 201 turbo-jet adapted for marine use with materials suitable for operation in a salt-laden atmosphere, coupled to a single-stage power turbine and output shaft. Reference should be made when reading these notes to the following brochures: (a) Marine Olympus power unit for hyrofoils and planing craft MGT.4 2 December 1962. (b) Marine Olympus TBD.8 8 August 1961.

Bristol Siddeley Limited, Ansty: MoD(N) supported Marine engine Research & development for 1967 - 1972 Industrial & Marine Division  PA1716/5/11/9/17  October 1966

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With the present programme for HMS Exmouth, ordering of machinery for Type 82 and future prospects for Type 19, the Bristol Siddeley development programme must continue apace, not only to back up these programmes, but also to proceed with active research and development for future prospects. 1 Marine olympus; 2 reversing turbines; 3 Shock barge tests; 4 Centaur; 5 Water jet propulsion

Ministry of Defence Ship Department (Marine Engineering division Navy): Operation of main machinery HMS Exmouth  PA1716/5/11/9/18  1967

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Contents:
TP.709. This document is the property of Her Britannic Majesty's Government, and is issued for the information of such persons only as need to know its contents in the course of their official duties. Section 1. general layout. Section 2 Olympus gas turbine; gas generator axuiliary systems. Power turbine. Section 3 Proteus gas turbine. Section 4 Main gearing. Section 5 SSS clutches. Section 6 Shaft break. Section 7 Propeller

Bristol Siddeley Limited: Marine Olympus power unit for hydrofoils and planing craft. general description  PA1716/5/11/9/19  December 1962

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Contents:
MGT.42.The Bristol Siddeley Marine Olympus power unit is specifically designed for hydrofoil, planing, and displacement craft

Rolls-Royce Limited: Marine gas turbines. General specification No.20100 for TM.3 Marine propulsion module  PA1716/5/11/9/20  March 1969

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Contents:
Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. The TM.3 Module comprises an Olympus 2017 gas generator mounted on a base frame containing the 325/326 power turbine, the whole enclosed in an acoustic enclosure which is extended forward to form an intake space containing an air inlet cascade bend. The 2017 Olympus gas generator comprises a five-stage low-pressure compressor, and a seven-stage high-pressure compressor, being independently driven by a single-stage turbine, via a coaxial shaft. The combustion section is of the can-annular type containing 8 flame tubes each having a Duplex burner

Rolls-Royce Limited: Guidance notes for the design of gas turbine intakes and exhausts for ships  PA1716/5/11/9/21  February 1971

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Contents:
PSR.160 Issue 3. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty

Rolls-Royce Limited: Olympus TM.3 machinery supply proposal  PA1716/5/11/9/22  October 1971

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Contents:
MGT.5004. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. Development of the Marine Olympus started in 1962, and the engine was installed in the first Finnish gunboats in 1967, using a Brown-Boveri power turbine. In 1968 the Olympus went to sea in HMS Exmouth using a Rolls-Royce power turbine

Rolls-Royce Limited: Olympus TM.3 propulsion module. Mandatory installation requirements  PA1716/5/11/9/23  February 1972

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Contents:
MGT.5012. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty

Rolls-Royce Limited: Olympus liquid fuel contol system generating applications. Fuels to R-R specification  PA1716/5/11/9/24  5 January 1971

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Contents:
Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. Issued by technical Services (Systems) Department. The sytem has been designed for running an Olympus engine on liquid fuel; and is comprised of the following: Power speed controller, electrically driven starting fuel pump, engine filter, engine driven fuel pumps, HSSOC, distributor, burners, electrical governor, and gagnetic pick-up. Fuel which is required at the engine filter at a pressure between 5-20psig is delivered by two variable diplacement fuel pumps driven from the engine high-pressure and low-pressure compressors through the high-speed shut-off cock and flow distributor to the burners

Rolls-Royce Limited: Olympus Type 22 Model uptake tests with vortex generators TSR.583  PA1716/5/11/9/25  22 January 1974

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Contents:
TGD/DB/ID/660/947. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. A series of model tests has been completed on the Olympus Type 22 Option 'C' Model uptake with Vortex generator plates, positioned in the TM. 3 exhaust

Rolls-Royce Limited: Development of the Olympus and Tyne gas turbines for marine propulsion  PA1716/5/11/9/26  January 1969

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Contents:
MGT.1040. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. Following the Ministry of defence decision to install Olympus/Tyne COGOG machinery in all new frigates and destroyers, Rolls-Royce were given a contract to design and build three prototypes of a free power turbine version of the Tyne Mk.62. Subsequently, a production order for these units for installation in the Type 42 and Type 21 destroyers and frigates will be placed by the MoD who have officially notified R-r of their intention to place such an order

Rolls-Royce Limited: Marine Olympus 593 for naval ships (provisional)  PA1716/5/11/9/27  1973

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Rolls-Royce Limited: Specification for Olympus TM.3B propulsion module. DG Ships  PA1716/5/11/9/28  20 November 1972

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Contents:
Ref: 215/313/09/03. 3.15.1. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty

Rolls-Royce Limited: Olympus TM.3B for warships. Design philosophy  PA1716/5/11/9/29  1979

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Contents:
MGT.5215. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. During the past year, Rolls-Royce have completed a detailed feasibility study of a new 15,000 hp naval engine, the SM.1A. Although this engine is intended for different appications from the Olympus it will still, of course, have to stand up to the same rigorous conditions of naval service

Rolls-Royce Limited: Type 43 propulsion machinery shore trials project  PA1716/5/11/9/30  1971 - 1979

Rolls-Royce Limited: Type 43 CCH shore trials facility. Circulating water system  PA1716/5/11/9/30/1  2 February 1971

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Contents:
Y.274. Part 1. section 4

Rolls-Royce Limited: Drawing TFE.79484/001 - 66 Test House prop arrangement of Type 43 machinery shore trials facility  PA1716/5/11/9/30/2  11 June 1979

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Contents:
Sheet 1 Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty

Rolls-Royce Limited: Type 43 propulsion machinery shore trials project. Roll-Royce submission in response to the statement of requirements  PA1716/5/11/9/30/3  March 1979

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Contents:
Ref: 1620/087/34. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty. Y.274. Part 1 section 4: CCH Shore trials circulating water system. Drawing TFE.79484/001 11/06/79: 66 Test House Prop arrangement of Type 43 machinery shore trials

Rolls-Royce Limited: Marine Olympus TM.3B propulsion module. Mandatory installation requirements  PA1716/5/11/9/31  April 1979

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MGT.5012/3. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty

Rolls-Royce Limited: Marine Olympus & Tyne condition monitoring and fault diagnosis. Description and definition of extent of standard supply  PA1716/5/11/9/32  June 1980

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MGT.5368. Rolls-Royce Limited Industrial and Marine Gas Turbine Division, Ansty

File of photographs of Olympus engines and naval cruisers  PA1716/5/11/9/33  1960s

153 Items

Brochure: Gas Turbines for Marine Propulsion  PA1716/5/11/9/34  1980

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Article: Gas Turbines in the Royal Navy, 1965 - 1969  PA1716/5/11/9/35  c. 1960s

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The Institute of Marine Engineers: Transactions, The Bristol Siddeley Olympus Marine Gas Turbine  PA1716/5/11/9/36  May 1967

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Press Cuttings from Home and Overseas on the Diesel Powered Fast Patrol Boats for the Royal Malayan Navy  PA1716/5/11/9/37  1960s

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Brochure: Marine Olympus TM3 Module  PA1716/5/11/9/38  1973

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Article from 'Marine Engineer and Naval Architect': The selection of machinery for naval frigates and destroyers  PA1716/5/11/9/39  November 1969

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Marine Gas Turbine News: £10 million in orders from France, Holland and Denmark  PA1716/5/11/9/40  October 1974

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Article from 'The Engineer': Gas turbines displacing steam in new fighting ships  PA1716/5/11/9/41  February 1970

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Brochure: Olympus Marine Power  PA1716/5/11/9/42  1967

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Article from The Institute of Marine Engineers: The Bristol Siddeley Olympus Marine Gas Turbine  PA1716/5/11/9/43  January 1967

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Article: Removal of LP Casing  PA1716/5/11/9/44  c. 1970s

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Article: Marine Development of the Olympus Engine by B.H. Slatter  PA1716/5/11/9/45  1966

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Navy Supplement: Armada Republica Argentina, Type 42 Guided Missile Destroyer  PA1716/5/11/9/46  c. 1970s

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Article: Olympus Powered Warships of the 1970s by G.G. Connor  PA1716/5/11/9/47  1970s

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Article: Rolls-Royce Gas Turbine Propulsion Systems in Dutch Designed Warships, by G.G. Connor  PA1716/5/11/9/48  July 1976

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Article: Rolls-Royce News, HMS Exmouth, The World's First Fully Operational Gas Turbine Warship is Accepted by the Royal Navy  PA1716/5/11/9/49  c. 1970s

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Article: Olympus Power for Large Warships. For 'The Diplomatist'  PA1716/5/11/9/50  20 March 1969

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Development of the Olympus and Tyne Gas Turbines for Marine Propulsion  PA1716/5/11/9/51  c. 1970s

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Volume of press cuttings concerning marine gas turbine engines  PA1716/5/11/9/52  1960s - 1970s

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File of publicity material concerning marine gas turbines  PA1716/5/11/9/53  1970s

8 Items

Volume of press cuttings concerning marine gas turbine engines  PA1716/5/11/9/54  1960s - 1970s

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File of photographs: Marine Olympus and Proteus  PA1716/5/11/9/55  c. 1960s

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Photographs of the A.S.M. entry for Warships Week  PA1716/5/11/9/56  1942

2 photographs

Contents:
Includes staff; black and white.

Article: British Gas Turbines  PA1716/5/11/9/57  21 December 1945

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Contents:
Article from 'Aeronautical Engineering'; negative; 7 pp.

Olympus 593 Industrial development  PA1716/5/11/10  1963 - 1978

Rolls-Royce draft report: The Olympus 593 Concorde engine) industrial & marine application  PA1716/5/11/10/1  24 October 1963

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The use of aero gas turbines for marine propulsion and as the power source for electricity generation and other industrial purposes is becoming of ever increasing interest. This is because of its compactness, versatility and reliability of these engines compared with the more conventional bulky units of the same power

Rolls-Royce Limited Industrial & Marine Division: Sales forecast for Olympus B & C power generation  PA1716/5/11/10/2  30 October 1969

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Memo by J Chesterfield. My forecast of 593 sales was based primarily on SRI's views both of total potential for all gas generators of 50 MW and over and on their assessment of the likely percentage to go to an heavy duty Rolls-Royce 75 MW turbine modified by the lower market appeal of the double-ended 593. The main sales of the 593, would in my view, be for the double-ended version

Rolls-Royce Limited Industrial & Marine Division: Sales potential for Olympus 593 in power generation  PA1716/5/11/10/3  13 January 1970

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Report by J Chesterfield. In my memo of the 29 October 1969, I forecast an average of 15 sales per annum at £365,000 and approximately 32 sales per annum at £285,000. From discussions that have taken place since then, it is apparent that the selling price of the 593 cannot be lower than about £365,000, so it is the prediction of 15 sales per annum on which attention is now focused

Rolls-Royce Limited Industrial & Marine Division: Olympus 593 for industrial electrical generation sales  PA1716/5/11/10/4  16 January 1970

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Memo from A Jubb. The requirement is that the engine shall be used for periods between 500 and 2,000 hours per year on liquid or gas fuel shall be suitable for rapid starts (two minutes to full power maximum), should have an overhaul life of between 2,000 and 4,000 hours. The hours per start are expected to be between one (unlikely), probably two or three as normal and occasionally to be up to ten. These engines are expected to be sold in three situations. (a) As emergency crash start use for auxiliary

Rolls-Royce Limited IMD. Letter to Mr M T Wodstock, Ministry of Technology: M.45H and 593 engines  PA1716/5/11/10/5  16 February 1970

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Contents:
Our ref: AE/SEC. Referring to our telephone conversation of this morning, I enclose herewith copies of two brochures on the M.45H engine. In addition I enclose brochures on the Olympus 593, which is the engine for Concorde

Rolls-Royce Limited IMD internal memo from Mr DE Williams: The 593 as an industrial engine  PA1716/5/11/10/6  29 September 1970

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Contents:
From Mr DE Williams to Mr GT Barker. The 593 as an industrial engine is still a Future Projects responsibility and will remain so until it becomes a committed project. Mr Daish has, passed your request (your memo GTB.G220 of 16 September) for broad brush performance on the industrial 593, on to me. The attached performance data refers to an engine which is at present Concorde flight standard modified by the incorporation of the aero LP compressor, and a blade cooling standard schedule in the Mk.602 engine. The turbine entry temperature have been chosen to keep the HP blade max surface temperature to the value at which existing Olympus 201 engines are run. The data is rather better than broad brush and is unlikely to be updated in the next few months

Rolls-Royce Limited IMD internal memo from Mr AWT Mottram: 593 brochure changes  PA1716/5/11/10/7  17 December 1970

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Contents:
Mr AWT Mottram to Mr O Noel. I think it would be a good idea to mention the industrial and marine possibilities of the Olympus 593. However, at the moment we are not certain what its performance will be in these applications and are, therefore, only giving general indications of its probable output at the present time

Rolls-Royce Limited IMD internal memo from Mr JN Hurst: Olympus 593 for the United States  PA1716/5/11/10/8  21 April 1971

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Mr JN Hurst to Mr A Judd. It is apparent that the peaking generation market in the United States is moving faster than I anticipated, this is due to the great success which general Electric have had in marketing their new Frame 7 machine with reported sales standing at 97. Westinghouse are lagging very far behind with the W.501 and the GE business has been gained at both the expense of Westinghouse and Pratt & Whitney and particularly at the expense of Westinghouse. Several of our main contractor partners have urged us to see whether we could introduce the Olympus 593 at an earlier date than 1976

Rolls-Royce (1971) Limited IMD. Company confidential: Olympus 593 Meeting Friday 2 July 1971  PA1716/5/11/10/9  2 July 1971

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Contents:
Present: Mr RT Whitfield, Mr WH Lindsey, Mr AH Fletcher, Mr A Judd, Mr CEM Preston, Mr T Powell BED. The following decisions were reached: 1 WHL to define the equirements for a first demonstrator gas generator (500 hours at peak lopping conditions). 2 AJ and TP to agree the probable specification for production engines. 3 BED to provide an indicated production engine cost based on the agreed specification,and to give to give estimates of escalation rate based on standard formula in the Inter-Divisional terms of trade. 4 WHL to draw up a programme for production of a power turbine, skid, and controls. 5 CEMP to provide a brochure for use by BED with the Ministry of Aviation, and by IMD for discussion with CEGB. 6 Target dates: (a) 593 brochure to be availabble by the end of August 1971. (b) Project decision, with Main Board approval, September/october 1971. (c) IMD to start power turbine design October 1971. (d) BED to provide demonstrator gas generator by end of 1972. (e) Commence demonstrator running at Hams Hall July 1973.

Rolls-Royce (1971) Limited IMD: Olympus 593 industrial applications  PA1716/5/11/10/10  3 April 1970

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Memo from PG Cockell to AJ Mottram. Ref: JAW/PGC/557. John reports that Allis Chalmers considered that their target price would be $70 per kilowatt. This is usefuly higher than the figure of $60 per kilowatt which you have mentioned to us and I wonder whether you have any comments on this report?

Telex from Cooper-Bessmer, Ohio, USA to Rolls-Royce (1971) Limited IMD: Olympus 593 industrial performance information  PA1716/5/11/10/11  13 July 1971

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Contents:
Sender: J Herschel-Shorland (JH-S 288). Following on Stoke's telex 387 concerning outstanding items from Whitfield, Blakely meeting in May. Most items have been covered in letter of 2 July from Mr Inglis to Roy Green and only outstanding item is Olympus 593 performance information, this currently being reassessed to determine data associated with peak rating target power of 46MW. This data should be available in September. In the meantime, preliminary figures for guidance purposes only as follows: For 46 MW ISA conditions; Air mass flow 420 lbs per second. Temp at entry to power turbine, 1020degK. Pressure at entry to power turbine, 48 PSIA

Rolls-Royce (1971) Limited IMD internal memo: Olympus 593 industrial engine for CEGB  PA1716/5/11/10/12  13 August 1971

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Contents:
From Mr JN Hurst to Mr RT Whitfield. At a recent meeting with CEGB to discuss the Olympus engineering and overhaul, the subject of the Olympus 593 was raised. Someone in CEGB indicated that the CEGB is not interested in this engine

Rolls-Royce (1971) Limited IMD internal memo: Olympus 593 sales forecast  PA1716/5/11/10/13  13 September 1971

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Contents:
From Mr AWT Mottram to Mr CEM Preston. In order to prepare an outline profit plan for the 593 by mid-October, I will need a sales forecast and market price indications for a gas generator and shaft power package. An indication of the electricity of the market as against price will be necessary. Would you please supply these. They will do about the end of September

Rolls-Royce Limited IMD internal memo: Olympus 593 gas transmission  PA1716/5/11/10/14  21 September 1971

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Contents:
From Mr CEM Preston to MR A Whitfield. I proposed in my note to you of the 20 July that we should endeavour to get a 593 into base load operation on a gas line in 1974. I suggest that one place where we might lodge this would be with Gasunie, because they were known to be wanting larger units of power in the future

Rolls-Royce Limited IMD internal memo: Olympus 593 Industrial forecast  PA1716/5/11/10/15  14 October 1971

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Contents:
This forecast is made on the assumption that: (a) A demonstrator is commissioned with CEGB in early 1974, and production engines can be delivered late 1975 for power generation. (b) A gas demonstrator is commissioned in late 1974, and production engines can be delivered for base load gas-fuelled applications from mid-1976. (c) Marine engines can be delivered from 1977. (d) Price is competitive. Our best estimate of the maximum competitive ex-works price, which applies to both the power generation and the oil and gas market, is £450,000 at 1973 price levels. Price is probably less critical for marine applications. Forecasts are given showing the estimated effect on sale of price increases or reductions.

Rolls-Royce (1971) Limited IMD internal memo: Olympus 593 market forecasts and brochure. Meeting held at Ansty, Friday 1 October 1971  PA1716/5/11/10/16  4 October 1971

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Rolls-Royce (1971) Limited IMD internal memo: Olympus 593 probable shrinking market for electrical generation in the future  PA1716/5/11/10/17  23 December 1971

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Contents:
From Mr JN Hurst to Mr J Dent. Reference your JD:ENG of 20 December 1970. There is an assumption in your last paragraph which requires examination, namely that the sales of gas generators are insensitive to the effort which we put into supplying power turbines. In my opinion an endeavour on our behalf (as Rolls-Royce) to supply the power turbine in a high proportion of cases is likely to significantly reduce sales of gas generators

Rolls-Royce (1971) Limited IMD Company confidential: The case for the Industrial Olympus 593  PA1716/5/11/10/18  August 1974

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Contents:
DEW/RB/HJW

Rolls-Royce Limited IMD: Industrial Olympus 593 packaged set standard price economic  PA1716/5/11/10/19  1 January 1978

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Rolls-Royce Limited IMD: Second review of the case for the Industrial Olympus 593  PA1716/5/11/10/20  September 1978

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Rolls-Royce Limited IMD: Development cost plan for Industrial Olympus 593 gas generator and packaged generating set  PA1716/5/11/10/21  October 1978

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Contents:
Ref: DCP.095/ST.2/01

Rolls-Royce (1971) Limited IMD Company confidential: Olympus 593 Industrial inter-divisional specification  PA1716/5/11/10/22  c. 1978

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Contents:
Ref: IDR.001

Rolls-Royce Limited IMD Company confidential: Olympus 593 Industrial gas generator. Specification  PA1716/5/11/10/23  April 1978

1 Item

Contents:
Ref: IGT 5270

Rolls-Royce Limited Aero Division Bristol: EPD.1109 Industrial 593 engine. Rig development programme for low-pollution combustor  PA1716/5/11/10/24  November 1977

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Contents:
The current aero standard of combustor cannot be developed to sufficiently low-pollution levels to meet anticipated regulations for industrial engines. Operation on liquid or gaseous fuels is now also a recognised requirement of industrial gas generators

U.S. Engine Repair Bass and Spairs Distribution Study for the RB.211 and Olympus 593 Engines  PA1716/5/11/10/25  3 March 1969

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Contents:
Report from Booz, Allen and Hamilton Management Consultants, for Rolls-Royce Limited, Derby, England.

Olympus 593 Industrial development. Press cuttings  PA1716/5/11/11  1971 - 1998

Rolls-Royce Olympus 593 goes industrial in 1981  PA1716/5/11/11/1  31 March 1978

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Contents:
Electrical Review Vol.202 No.12

Concorde 593 super engine to be sound base in industry  PA1716/5/11/11/2  c. 1978

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Contents:
Offshore Oil

Concorde engine comes down to earth  PA1716/5/11/11/3  April 1978

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Contents:
Energy international

Concorde engines light up industry  PA1716/5/11/11/4  3 April 1978

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Contents:
Engineering Today

How they are giving you supersonic power to run your business  PA1716/5/11/11/5  May 1978

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Contents:
Achievement

Concorde engine becomes a generator  PA1716/5/11/11/6  c. 1978

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Contents:
Unknown source

Concorde engine illustration with caption  PA1716/5/11/11/7  c. 1978

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Contents:
Aramco has expressed interest in the 100 MW package power stations that Rolls-Royce can offer with two industrial Olympus 593 gas generators operating in tandem

Hundred MW power units developed from Concorde engines  PA1716/5/11/11/8  April 1978

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Contents:
International Power Generation

Rolls-royce jet engine developed now produces 66,000 hp industrial gas turbine power  PA1716/5/11/11/9  May 1978

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Contents:
Canadian news clipping

New roll for Concorde engine  PA1716/5/11/11/10  July 1978

1 Item

Contents:
Physics in Technology

Concorde engine for electrical generation in 1981  PA1716/5/11/11/11  1978

1 Item

Contents:
Diesel Engineering

Electric light and power. New gas turbine uses SST engine  PA1716/5/11/11/12  June 1978

1 Item

Contents:
Wall Street Journal

Concorde-style engine at Cardiff Road Watford  PA1716/5/11/11/13  20 February 1976

1 Item

Financial Times: North Sea generating sets  PA1716/5/11/11/14  c. 1980

1 Item

Diesel Engineering: Rolls-Royce package sales in Middle East  PA1716/5/11/11/15  1977

1 Item

Electrical World: Rolls-Royce supplies the power and the station, too  PA1716/5/11/11/16  15 December 1976

1 Item

Murchison Field Production Platform  PA1716/5/11/11/17  c. 1980s

1 Item

Pipe Line Industry: Generating sets are nearly complete  PA1716/5/11/11/18  May 1979

1 Item

Offshore Services: Industrial Olympus Engine, generating sets  PA1716/5/11/11/19  May 1979

1 Item

International Petroleum Times: Generator sets for Murchison  PA1716/5/11/11/20  May 1979

1 Item

Electrical Review: Vol.199, No.3, Packaged gas turbine power station  PA1716/5/11/11/21  16 July 1976

1 Item

Energy International: Coal gasifier projects gather momentum  PA1716/5/11/11/22  March 1977

1 Item

Rolls Turbines for Murchison  PA1716/5/11/11/23  c. 1970s

1 Item

Gas Turbine World: Malawi 20-Mw set shipped and running in six months  PA1716/5/11/11/24  May 1976

1 Item

Electrical Review: Vol.204 No.15, Big heat pump could upgrade power station waste heat  PA1716/5/11/11/25  20 April 1979

1 Item

Watford Evening Echo: Rolls-Royce win big order for gas pumping engines  PA1716/5/11/11/26  26 January 1976

1 Item

Diesel and Gas Turbine Progress Worldwide: 50 Mw Gas Turbine From Rolls-Royce  PA1716/5/11/11/27  June 1978

1 Item

Coventry Evening Telegraph: Industrial Olympus generating sets  PA1716/5/11/11/28  April 1979

1 Item

Offshore Europe: SK30M Compact Gas Turbine  PA1716/5/11/11/29  September/October 1977

1 Item

From Insumat to Iran: 20MW Rolls-Royce Olympus gas turbine powered generating set  PA1716/5/11/11/30  c. 1998

1 Item

Energy International: Rolls-Royce Ltd, Olympus powered SK generating sets  PA1716/5/11/11/31  February 1979

1 Item

International Power Generation: Gas turbine generating sets to power Conoco - Murchison offshore rig  PA1716/5/11/11/32  April 1979

1 Item

Diesel and Gas Turbine Progress Worldwide: Turbine Generating Sets Power North Sea Platform  PA1716/5/11/11/33  May 1979

1 Item

Diesel and Gas Turbine Progress: Packaged Turbine Generating Sets from Rolls-Royce  PA1716/5/11/11/34  May 1973

1 Item

The Daily Mercury: Hospital Bridge, gas-turbine engine  PA1716/5/11/11/35  1975 - 1976

1 Item

Diesel and Gas Turbine Progress: 100 Mw Gas Turbine Peaking Unit  PA1716/5/11/11/36  January 1971

1 Item

Rolls-Royce Customer Training Centre Ansty: Course notes  PA1716/5/11/12  1965 - 1978

Rolls-Royce Customer Training Centre Ansty: Course notes. HMS Exmouth. TP 657 Marine Olympus Type TM1. General description  PA1716/5/11/12/1  November 1967

1 Item

Contents:
Ministry of Defence.Ship Department. This book is the property of HM Government. Gas generator; Power turbine; Mk.2013 gas generator; turbine associate equipment

Rolls-Royce Customer Training Centre Ansty: Course notes TP 321 Marine Olympus Type TM3B General description  PA1716/5/11/12/2  c. 1978

1 Item

Contents:
Ref: 40726. Olympus Mk.2013 twin spool, axial flow gas generator; gas generator and power turbine TP321 & associated equipment

Rolls-Royce Customer Training Centre Ansty: Course notes. Marine Olympus Type TM3B General description  PA1716/5/11/12/3  c. 1978

1 Item

Contents:
Ref: 40726. The marine Olympus gas generator type 2017 is an axial-flow, twin-spool, turbo-jet providing thrust for the separately mounted power turbine. The low pressure (LP) and high pressure (HP) compressors are driven independently by their own single-stage turbines through co-axial shafts

Rolls-Royce Customer Training Centre Ansty: Course notes. Marine Olympus Type TM3B General description  PA1716/5/11/12/4  August 1978

1 Item

Contents:
Introduction to gas turbine and the 'free' power-turbine principle in general, and the TM3 Propulsion Module in particular

Rolls-Royce Customer Training Centre Ansty. Instructional notes: 17.5/20MW Olympus turbo-generator installed at Tilbury for the Central Generating Electricity Board  PA1716/5/11/12/5  1965

1 Item

Course Notes on TP 657 Marine Olympus Gas Turbine Type TM1, HMS Exmouth  PA1716/5/11/12/6  1968

1 item

Contents:
Issued by Rolls-Royce Customer Training Centre, Ansty, Coventry, England.

Bristol Siddeley Power Division: Outside Erection Department - Power station master log books  PA1716/5/11/13  6 November 1963 - 27 November 1968

Contents:
Central Electricity Generating Board: Beddington Farm Lane, Croydon

Bristol Siddeley Power Division: Power station master log book. Olympus industrial gas turbine.  PA1716/5/11/13/1  6 November 1963 - 27 November 1963

1 Item

Contents:
Central Electricity generating Board: Beddington Farm Lane, Croydon. Croydon 1 handing over date 6 November 1963. Croydon 2 handing over date 27 November 1963 Croydon 1: One 70MW turbo-generator set; Croydon 2: One 70MW turbo-generator set

Bristol Siddeley Power Division: Outside Erection Department - Power station master log book. Olympus industrial gas turbine.  PA1716/5/11/13/2  4 September 1964 - 27 September 1964

1 Item

Contents:
Central Electricity Generating Board: Hoddesdon Lane, Herts. Ryehouse 1 handing over date 4 September 1964; Ryehouse, 2 handing over date 25 September 1964 Ryehouse 1: One 70MW turbo-generator set; Ryehouse 2: One 70MW turbo-generator set

Bristol Siddeley Power Division: Outside Erection Department - Power station master log book. Olympus industrial gas turbine.  PA1716/5/11/13/3  16 October 1964

1 Item

Contents:
Central Electricity Generating Board: Dunfermline Scotland. Townhill 1 & 2 handing over date 18 October 1964 Townhill 1: One 70MW turbo-generator set; Townhill 2: One 70MW turbo-generator set

Bristol Siddeley Power Division: Outside Erection Department - Power station master log book. Olympus industrial gas turbine. Jersey Power Station: One 17.5MW turbo-generator set  PA1716/5/11/13/4  31 December 1963

1 Item

Contents:
Central Electricity generating Board. Queen's Road, St Helier, Jersey. Jersey Power station handing over date 31 December 1963

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Proteus Industrial generator sets. Schachtbau Lingen: Three 3MW Generator set  PA1716/5/11/13/5  31 July 1964

1 Item

Contents:
Kloekner Humboldt Deutz Az. Handing over date 31 July 1964

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book: Tilbury 'B' No.1: One 17.5MW Turbo-alternator set; Tilbury 'B' No.2: One 17.5MW Turbo-alternator set; Tilbury 'B' No.3: One 17.5MW Turbo-alternator set; Tilbury 'B' No.4: One 17.5MW Turbo-alternator set;  PA1716/5/11/13/6  1 January 1966

1 Item

Contents:
Central Electricity generating Board: Tilbury Port Road, Tibury, Essex. Tilbury 'B' Nos.1-4 handing over date 1 January 1966

Bristol Siddeley Engines Limited Power Division: Outside Erection Department. Power station master log book: Olympus Industrial gas turbines. Ferrvbridge 'C' No.1: One 17.5MW Turbo-alternator set; Ferrvbridge 'C' No.2: One 17.5MW Turbo-alternator set; Ferrvbridge 'C' No.3: One 17.5MW Turbo-alternator set; Ferrvbridge 'C' No.4: One 17.5MW Turbo-alternator set  PA1716/5/11/13/7  24 May 1965 - 4 September 1967

1 Item

Contents:
Central Electricity Generating Board: Knottingley, Yorkshire. Ferrybridge 'C' No.1 handing over date 24 may 1965; Ferrybridge 'C' No.2 handing over date 28 February 1966; Ferrybridge 'C' No.3 handing over date 28 November 1966; Ferrybridge 'C' No.4 handing over date 4 September 1967

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Olympus Industrial gas turbines. Townhill master log from January 1966  PA1716/5/11/13/8  4 January 1966 - 1 August 1969

1 Item

Contents:
Central Electricity Generating Board: Dunfermline Scotland

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book: Proteus Industrial gas turbines. Oldbury on Severn Power Station: Three 3MW sets  PA1716/5/11/13/9  1964 - 1966

1 Item

Contents:
Oldbury on Severn, Gloucester

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Proteus Industrial gas turbine: Las Palmas  PA1716/5/11/13/10  19 September 1966 - 1 April 1967

1 Item

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Lourenco Marques: One 17.5MW Olympus generating set  PA1716/5/11/13/11  19 October 1965 - 30 March 1966

1 Item

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Proteus industrial gas turbine Ras Abu Aboud Power station; One 3MW transportable generating set  PA1716/5/11/13/12  11 August 1966 - 20 January 1967

1 Item

Contents:
Government of Qatar

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Proteus industrial gas turbine RAF Aden: Three 3MW turbo-alternator sets plus one spare 'on-site' engine  PA1716/5/11/13/13  12 September 1963 - 22 November 1963

1 Item

Contents:
Air Ministry for RAF Station Khormksar, Aden

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Olympus industrial gas turbine. Eggborough Power station: Four 17.5MW sets  PA1716/5/11/13/14  1965

1 Item

Contents:
Central Electricity Generating Board: Whitley Bridge, near Goole, Yorkshire

Bristol Siddeley Engines Limited Power Division: Outside Erection Department - Power station master log book. Killingholme  PA1716/5/11/13/15  13 March 1967 - 29 March 1968

1 Item

Contents:
Killingholme, East Holton, Lincolnshire

Bristol Siddeley Engines Limited Industrial Division: Outside Erection Department - Power station master log book. Ironbridge 'C' Power Station: 2 17.5MW Olympus Gas Turbo-generator sets  PA1716/5/11/13/16  1967

1 Item

Contents:
National Power

Bristol Siddeley Engines Limited. Industrial Division: Outside Erection Department - Power station master log book. Aberthaw B Power Station: Two 17.5MW Olympus Gas Turbo Alternators  PA1716/5/11/13/17  4 October 1965 - 19 January 1968

1 Item

Contents:
National Power: Gileston, near Barry, Glamorgan

Bristol Siddeley Engines Limited. Industrial Division: Outside Erection Department - Power station master log book. Ratcliffe Power Station: Four 17.5MW Olympus Gas Turbo Alternator sets  PA1716/5/11/13/18  1966 - 1968

Contents:
Powergen: Ratcliffe-on-Sour, Nottinghamshire

Industrial and Marine Division  PA1716/5/11/14  [n.d.]

Admiralty Engineering Laboratory: Mechanical impedance measurements Marine Olympus TM1 power turbine  PA1716/5/11/14/1  September 1970

7 Items

Contents:
This document is the property of Her Majesty's Government and crown copyright is reserved

Assembly Procedure: B.S. 2101 Power Turbine  PA1716/5/11/14/2  June 1961

1 Item

Rolls-Royce Industrial Olympus 'C' Gas Generator Performance  PA1716/5/11/14/3  September 1974

1 Item

Power Division Report  PA1716/5/11/14/4  June 1963

1 Item

General Description: 35 Megawatt Turbo-Generator  PA1716/5/11/14/5  1966

1 Item

Memorandum: The Place of the Gas Turbine in an Electrical Generation System  PA1716/5/11/14/6  August 1960

1 Item

Flexible Diaphragm Couplings and Transmission Shafts for Rolls-Royce FS80 Power Turbine  PA1716/5/11/14/7  April 1974

1 Item

Olympus Engine Component Lives Reports  PA1716/5/11/14/8  1974 - 1978

14 Items

Olympus Engine Combustion Chamber Flame Tube Reports  PA1716/5/11/14/9  1975 - 1977

8 Items

Olympus Engine Control System Reports  PA1716/5/11/14/10  1974 - 1978

1 Item

Olympus Engine TSR Performance Reports  PA1716/5/11/14/11  1978

2 Items

Olympus Engine Thermal Paint Reports  PA1716/5/11/14/12  1979

1 Item

Olympus Engine Gas Generator Technical Specifications Reports  PA1716/5/11/14/13  1978 - 1979

4 Items

Olympus Engine 2nd Turbine (LP) Reports  PA1716/5/11/14/14  1974 - 1978

1 Item

Olympus Engine Power Turbine Design Reports  PA1716/5/11/14/15  1975 - 1978

16 Items

Olympus Engine Fuel Pumps Reports  PA1716/5/11/14/16  1975 - 1978

2 Items

Olympus Engine Combustor Programmes and Reports  PA1716/5/11/14/17  1975 - 1978

1 Item

Olympus Engine Smoke and Pollution Reports  PA1716/5/11/14/18  1974 - 1977

1 Item

Olympus Engine Termination of 593 Programme Reports  PA1716/5/11/14/19  1978

6 Items

Industrial and Marine Division: Divisional Achievement  PA1716/5/11/14/20  20 March 1974

1 Item

Industrial and Marine Division: General Presentation  PA1716/5/11/14/21  March 1980

1 Item

Brochure: Gas Turbine World  PA1716/5/11/14/22  c. 1980s

1 Item

Brochure: Component Repair Technology  PA1716/5/11/14/23  1989

1 Item

Brochure: Rolls-Royce Offshore  PA1716/5/11/14/24  April 1980

1 Item

Brochure: Rolls-Royce Industrial Installations Worldwide, Issue 4  PA1716/5/11/14/25  July 1986

1 Item

Brochure: Industrial Gas Turbines  PA1716/5/11/14/26  September 1989

1 Item

Brochure: SK Compact Generating Sets  PA1716/5/11/14/27  c. 1970s

1 Item

Brochure: Rolls-Royce Range of SK Compact Generating Sets  PA1716/5/11/14/28  July 1981

1 Item

Brochure: Rolls-Royce plc, financial highlights  PA1716/5/11/14/29  March 1987

1 Item

Brochure: Component Repair Organisation Ansty  PA1716/5/11/14/30  August 1988

1 Item

Brochure: Industrial Gas Turbine Production Pass-off Test  PA1716/5/11/14/31  March 1981

1 Item

Brochure: Industrial and Marine Power  PA1716/5/11/14/32  1979

1 Item

Brochure: Gas Turbines for Mechanical Drive  PA1716/5/11/14/33  c. 1979

1 Item

Brochure: Power for the Nile Delta  PA1716/5/11/14/34  February 1983

1 Item

Brochure: Rolls-Royce Offshore  PA1716/5/11/14/35  June 1977

1 Item

Brochure: Gas Turbines for Electrical Generation  PA1716/5/11/14/36  1978

1 Item

Brochure: Ffestiniog Power Station  PA1716/5/11/14/37  1963

1 Item

Brochure: Industrial and Marine Gas Turbines  PA1716/5/11/14/38  1970

1 Item

Brochure: Industrial Olympus Gas Generator  PA1716/5/11/14/39  1972

1 Item

Brochure: Industrial and Marine Products  PA1716/5/11/14/40  March 1985

1 Item

Brochure: Olympus Industrial Power  PA1716/5/11/14/41  1967

1 Item

Brochure: Civil Engine Group  PA1716/5/11/14/42  1984

1 Item

Brochure: Power for an Island  PA1716/5/11/14/43  September 1982

1 Item

Brochure: In this age of detente...WHY NAVY  PA1716/5/11/14/44  c. 1970s

1 Item

Brochure: 17.5/20MW turbo generator  PA1716/5/11/14/45  1963

1 Item

File of publicity relating to industrial and marine gas turbines  PA1716/5/11/14/46  1970s

7 Items

Volume of publicity relating to industrial and marine gas turbines  PA1716/5/11/14/47  1960s - 1970s

1 Item

Volume of publicity relating to industrial and marine Olympus  PA1716/5/11/14/48  1960s - 1970s

1 Item

Brochure: Industrial Gas Turbines in the United Kingdom  PA1716/5/11/14/49  September 1987

1 Item

Brochure: Industrial and Marine Power  PA1716/5/11/14/50  1986

1 Item

Brochure: Industrial and Marine Gas Turbine Division and Bristol Engine Division, Recommended Road Routes  PA1716/5/11/14/51  c. 1970s

2 Items

Brochure: Industrial and Marine Division  PA1716/5/11/14/52  June 1972

1 Item

Brochure: United Kingdom, Power Generation, Department of Industry  PA1716/5/11/14/53  1979

1 Item

Brochure: Olympus Gas Generator, Heavy Maintenance  PA1716/5/11/14/54  1970

1 Item

Brochure: Gas Turbine World, Coberrow, a unique concept for major pipeline projects  PA1716/5/11/14/55  November 1977

1 Item

Brochure: Rolls-Royce, Power for an Island  PA1716/5/11/14/56  1987

1 Item

Brochure: SK Range Packaged Generating Sets  PA1716/5/11/14/57  October 1973

1 Item

Brochure: Rolls-Royce Guide to Cogeneration Systems  PA1716/5/11/14/58  May 1988

1 Item

Brochure: Offshore Power  PA1716/5/11/14/59  September 1987

1 Item

Brochure: Gas Turbine World  PA1716/5/11/14/60  November 1979

1 Item

Brochure: Industrial Gas Turbines  PA1716/5/11/14/61  March 1988

1 Item

Brochure: Rolls-Royce Industrial and Marine Gas Turbine Power  PA1716/5/11/14/62  1971

1 Item

Brochure: The Industrial and Marine Gas Turbine World of Rolls-Royce  PA1716/5/11/14/63  June 1984

1 Item

Brochure: Pumps and Compressors  PA1716/5/11/14/64  1965

1 Item

Brochure: Bristol Siddeley 35/40 megawatt turbo generator  PA1716/5/11/14/65  c. 1970s

1 Item

Brochure: Bristol Siddeley 70/80 megawatt turbo generator  PA1716/5/11/14/66  c. 1970s

1 Item

Leaflet: Rolls-Royce TM Series Marine Gas Turbine  PA1716/5/11/14/67  December 1978

1 Item

Brochure: Noval Power  PA1716/5/11/14/68  1983

2 Items

Leaflet: Marine Power  PA1716/5/11/14/69  September 1987

1 Item

Brochure: Marine Gas Turbines - 1967 Status  PA1716/5/11/14/70  November 1967

1 Item

Brochure: Rolls-Royce Marine Gas Turbines  PA1716/5/11/14/71  1972

1 Item

Brochure: Rolls-Royce Marine Power  PA1716/5/11/14/72  September 1984

1 Item

Brochure: Rolls-Royce Industrial and Marine Products  PA1716/5/11/14/73  1979

1 Item

Brochure: The philosophy of gas turbine propulsion for major naval vessels  PA1716/5/11/14/74  1971

1 Item

Brochure: Power for air, land and sea  PA1716/5/11/14/75  April 1989

1 Item

Guidance Notes: Fuels and Oils for use with Rolls-Royce Industrial and Marine Products  PA1716/5/11/14/76  June 1980

1 Item

International Defence Review: The Royal Navy's Invincible-class Cruisers  PA1716/5/11/14/77  1979

1 Item

Brochure: Industrial RB 211: On-site modular change and special task maintenance  PA1716/5/11/14/78  May 1986

1 Item

Brochure: RB211-22B, Technology and Description  PA1716/5/11/14/79  July 1980

1 Item

Brochure: The Marine RB.211, A High Performance Engine for Marine Propulsion  PA1716/5/11/14/80  July 1969

1 Item

Feasibility Study: Performance Data, RB 223 - 50HZ Power Turbine  PA1716/5/11/14/81  16 July 1974

1 Item

Combustion and Fuels  PA1716/5/11/14/82  November 1977

1 item

Contents:
Report by Rolls-Royce Limited.

200 M.W. (T) M.H.D. Generator - Bristol Siddeley Tender and C.E.G.B. Specification  PA1716/5/11/14/83  c.1964

1 item

Contents:
Report by Bristol Siddeley.

Olympus Drawings and Photographs  PA1716/5/11/15  [n.d.]

Arrangement Drawings: Olympus 593B, Bench Engine  PA1716/5/11/15/1  November 1965

1 Item

Arrangement Drawings: Olympus 301  PA1716/5/11/15/2  24 February 1964

1 Item

Arrangement Drawings: Olympus Marks 201, 202 and 203  PA1716/5/11/15/3  29 April 1964

1 Item

Arrangement Drawings: Olympus 200  PA1716/5/11/15/4  29 April 1964

1 Item

Arrangement Drawings: Olympus 301  PA1716/5/11/15/5  August 1961

1 Item

File of Olympus Drawings  PA1716/5/11/15/6  1950s - 1960s

12 Items

File of Olympus Photographs and Diagrams  PA1716/5/11/15/7  1960s

159 Items

File of Industrial Olympus and Industrial Proteus Photographs  PA1716/5/11/15/8  c. 1960s

1 Item

Bristol Siddeley 17.5 / 20 MW Generating Set Fuel Control Sytem  PA1716/5/11/16  20th Cent.

2 items

Contents:
2 identical drawings, one handcoloured.

Olympus Engines Reports and Engine Stress Investigations  PA1716/5/11/17  1959 - 1964

1 file

Contents:
Includes Strain Gauge Tests.

An Account of an Engineering Investigation into the Cause of an Aircraft Engine Failure  PA1716/5/11/18  30 January 1958

1 item

Olympus 320 Final Development Position  PA1716/5/11/19  15 June 1965

1 item

Contents:
Report on the final development state of the Olympus 320 engine at cancellation of the project.

Avon Engine  PA1716/5/12  [n.d.]

Course Notes: Industrial Avon - Gas Fuelled and Supplements for Liquid and Dual Fuelled  PA1716/5/12/1  19 August 1986

1 Item

Aero Engine Division, Engine Test Schedule: Avon Mk. 301  PA1716/5/12/2  1967

1 Item

Provisional Performance Data and Installation Notes: Avon Mk. 522, 524 and 525 Engines  PA1716/5/12/3  1957

1 Item

Aero Engine School Course Notes: Avon 100 Series  PA1716/5/12/4  1955

1 Item

Established Performance Data and Installation Notes: Avon Mk.202 Engine  PA1716/5/12/5  June 1958

1 Item

General Description: Industrial Avon Gas Generator  PA1716/5/12/6  February 1973

1 Item

The Industrial Avon Gas Generator Maintenance Philosophy and Experience  PA1716/5/12/7  November 1980

1 Item

Industrial RB211 and Avon gas generator condition monitoring  PA1716/5/12/8  November 1982

1 Item

Provisional Performance Data and Installation Notes: Avon R.A. 28 Rating Engine  PA1716/5/12/9  November 1953

1 Item

Aero Engine School Course Notes: Avon  PA1716/5/12/10  1964

1 Item

Customer Training Centre: Avon Industrial Practical Course Notes  PA1716/5/12/11  c. 1986

1 Item

Avon Mk.1533 Industrial Gas Generator Performance, Issue 2  PA1716/5/12/12  February 1967

1 Item

The Avon Mk.1535 Gas Generator  PA1716/5/12/13  March 1979

1 Item

General Description: Avon Gas Generator  PA1716/5/12/14  November 1968

1 Item

The Industrial Avon Gas Generator: Background and Experience  PA1716/5/12/15  April 1980

1 Item

Customer Training Centre Course Notes: Industrial Avon  PA1716/5/12/16  1969

1 Item

Report on Uprating of the Base Load Avon Generator from 10.4 MW to 13.4 MW  PA1716/5/12/17  October 1969

1 Item

A Compressor Test, Altitude and Airflow Facility for the People's Republic of China  PA1716/5/12/18  May 1974

1 Item

Brochure: Industrial Avon Gas Generator - Heavy Maintenance  PA1716/5/12/19  October 1978

1 Item

Engine Test Schedule: Avon Mk. 1533, Production Dual Fuel System  PA1716/5/12/20  1969

1 Item

Provisional Performance Data and Installation Notes: Avon R.A. Rating Engine  PA1716/5/12/21  November 1952

1 Item

Estimated Performance Data and Installation Notes: Avon R.A. 50 Rating Engine  PA1716/5/12/22  1950s

1 Item

Provisional Performance Data and Installation Notes: Avon R.A.24 Rating Engine  PA1716/5/12/23  October 1955

1 Item

Estimated Performance Data and Installation Notes: Avon Engine R.A. 29 Stage 3  PA1716/5/12/24  March 1957

1 Item

A Compressor Test Facility for the People's Republic of China  PA1716/5/12/25  February 1975

1 Item

Performance and Technical Features of the Industrial Avon gas generator variants  PA1716/5/12/26  June 1980

1 Item

Estimated Performance Data and Installation Notes: Avon R.A.29 Rating Engine  PA1716/5/12/27  December 1955

1 Item

Estimated Performance Data and Installation Notes: Avon Engine R.A.29 Stage 4 Performance Rating  PA1716/5/12/28  March 1957

1 Item

Established Performance Data and Installation Notes: Avon Mark 1 Engine  PA1716/5/12/29  1950s

1 Item

File of brochures concerning Avon Industrial Gas Generator  PA1716/5/12/30  1970s - 1980s

1 Volume

The Design and Operating Experience of a Mobile Gas Turbine with 16,000-HP Capability by D.R. Ritcey  PA1716/5/12/31  c. 1980s

1 Item

Press Release: Rolls-Royce Avons for German Power Stations  PA1716/5/12/32  17 February 1970

1 Item

Report: Hunter with Developed Avon  PA1716/5/12/33  c. 1980s

1 Item

Gas Turbines in the 1980s by C.E.M. Preston  PA1716/5/12/34  1977

1 Item

Brochure: Avon Gas Generator Heavy Maintenance  PA1716/5/12/35  1965 - 1978

3 Items

Avon Gas Generator Maintenance, Section 4: Checking and Setting the Air Flow Control System  PA1716/5/12/36  December 1973

1 Item

Technical Report: Avon RA.29, Effect of Capacity Reduction on Model Turbine Efficiency  PA1716/5/12/37  9 June 1959

1 Item

Industrial Avon: Gas Generator Operation and Control  PA1716/5/12/38  15 January 1972

1 Item

Engineering Liaison: Avon Industrial Engines Installation Brochure, Issue 3  PA1716/5/12/39  1966 - 1968

4 Items

Manual: Avon Hot-End Change  PA1716/5/12/40  March 1972

1 Item

OSCO - Iran: Heavy Maintenance Tools and Equipment for Avon Mark 1533 and Mark 1534  PA1716/5/12/41  17 October 1975

1 Item

Brochure: Avon Achievements  PA1716/5/12/42  c. 1970s

1 Item

Contents:
Photocopy

File of report on the fanned Avon  PA1716/5/12/43  1970s

1 Volume

M.45 Engine  PA1716/5/13  [n.d.]

File of photographs of M.45  PA1716/5/13/1  c. 1970s

187 Items

Contract Specification: M45H Turbofan for VFW Short Range Airliner  PA1716/5/13/2  September 1972

1 Item

Illustrated Parts Catalogue: M45H - 501  PA1716/5/13/3  1 June 1979

1 Item

Contract Report: M45 SD-O2  PA1716/5/13/4  1979

1 Item

General Description: M45H Turbofan  PA1716/5/13/5  May 1973

1 Item

General Description: M45H Turbofan  PA1716/5/13/6  August 1974

1 Item

M45H Turbofan for the VFW614 Airliner  PA1716/5/13/7  February 1967

1 Item

Development of the M45H Gas Turbine Engine as a Powerplane  PA1716/5/13/8  c. 1970s

1 Item

Contents:
Photocopy

File of publicity material relating to the M45  PA1716/5/13/9  1970s - 1980s

29 Items

File of arrangement drawings relating to the M.45  PA1716/5/13/10  1960s

2 Volumes

Gnome Engine  PA1716/5/14  [n.d.]

Bristol Siddeley Aero Engine School, Leavsden, Instruction Course Manual: Service and Maintenance Course Notes, Gnome H 1000  PA1716/5/14/1  1963

1 Item

General Description: B.S. Gnome Turbo Shaft Engine for Air Cushion Vehicles  PA1716/5/14/2  March 1964

1 Item

Technical Specification: Gnome H.1200 Turboshaft Engine  PA1716/5/14/3  October 1966

1 Item

Technical Specification: Rolls-Royce Gnome Marine Gas Turbine  PA1716/5/14/4  August 1967

1 Item

Course Notes: Gnome Hovercraft Installations - Series of Engines  PA1716/5/14/5  c. 1977

1 Item

Photographs of Gnome Engines  PA1716/5/14/6  c. 1960s

19 Items

Contents:
Contains related memorandum

Marine Gnome: Development Reports  PA1716/5/14/7  18 January 1971 - 6 April 1972

1 Volume

Preliminary Technical Specification: Gnome H1400-2, Turboshaft Engine  PA1716/5/14/8  December 1969

1 Item

Technical Specification: Gnome H1400, Turboshaft Engine  PA1716/5/14/9  March 1970

1 Item

Proposals for the Development of the Gnome Engine for Hovercraft Applications  PA1716/5/14/10  September 1965

1 Item

General Description: Gnome H 1000, Turboshaft Engine  PA1716/5/14/11  July 1963

1 Item

Bristol Siddeley Gnome Mk.510 and 610, Deep Field Servicing Requirements, Austria  PA1716/5/14/12  December 1966

1 Item

Technical Specification: Gnome H1200 Turboshaft Engine  PA1716/5/14/13  May 1971

1 Item

Technical Specification: Gnome H1400-1 Turboshaft Engine  PA1716/5/14/14  June 1972

1 Item

General Description: Gnome H 1200 Turboshaft Engine  PA1716/5/14/15  April 1963

1 Item

Maintenance Manual: Gnome R.R. Gn 1051 Turbo-Shaft Engines  PA1716/5/14/16  July 1965

1 Item

Report: Gnome 1301 Engine - Civil Rating  PA1716/5/14/17  18 June 1973

1 Item

Draft Maintenance Manual: Gnome H.1400  PA1716/5/14/18  May 1968

1 Item

Brochure: Westland Helicopters Limited, Wessex 50 Series  PA1716/5/14/19  c. 1960s

1 Item

Brochure: WG.13 Multi Purpose Helicopter  PA1716/5/14/20  c. 1960s

1 Item

Brochure: Gnome, Turboshaft Engine for Helicopters  PA1716/5/14/21  May 1965

1 Item

Brochure: Gnome for hovercraft  PA1716/5/14/22  1964

1 Item

Volume of press cuttings concerning Gnome engines  PA1716/5/14/23  1960s - 1970s

1 Item

File of publicity material concerning Gnome engines  PA1716/5/14/24  1960s - 1970s

6 Items

Orpheus Engine  PA1716/5/15  [n.d.]

Photographs of Orpheus cockpit, Hindustan Aircraft Ltd  PA1716/5/15/1  c. 1950s

12 Items

Bristol Siddeley Engines, Installation Liasion Department: Orpheus B.Or.3, Lightweight Jet Propulsion Engine  PA1716/5/15/2  January 1957

1 Item

Newspaper and Magazine Articles regarding Orpheus  PA1716/5/15/3  1958 - 1967

8 Items

Contents:
From 'Bristol Siddeley Review', 'Bristol Siddeley News' and 'Flight International'

Bristol Siddeley Engines, Installation and Liasion Department: Orpheus B.Or.12SR, Lightweight Turbojet Engine  PA1716/5/15/4  June 1958

1 Item

Derated Orpheus B.Or.12 Engine for Handley Page 113 Aircraft  PA1716/5/15/5  September 1958

1 Item

Orpheus Mark 803, Lightweight Turbojet Engine  PA1716/5/15/6  November 1958

1 Item

Bristol Siddeley Engines: Orpheus Mark 805 in Hunting Aircraft Limited H.126 Jet Flap Research Aircraft, Specification, Development Programme and Estimated Costs  PA1716/5/15/7  August 1959

1 Item

General Description: Marine Orpheus 1300  PA1716/5/15/8  April 1960

1 Item

Orpheus Mark 100, Lightweight Turbojet Engine, Performance  PA1716/5/15/9  May 1960

1 Item

Orpheus Mark 803F-12 for the Dassault 'Balzac V', Contract Specification  PA1716/5/15/10  August 1961

1 Item

Diagrams of Bristol Siddeley Orpheus 10001 E.C.U. Fuel System  PA1716/5/15/11  May 1961 - July 1961

4 Items

Bristol Siddeley Orpheus AS A 5750lb Thrust-Boost and Auxiliary Power Unit in the Boeing 737 Aircraft  PA1716/5/15/12  December 1967

1 Item

A New Proposal for the Orpheus with 5750lb Thrust-Boost for the Transall C160 Aircraft  PA1716/5/15/13  December 1967

1 Item

Rolls-Royce Orpheus Vectored-Thrust Engine for the CV-7A Buffalo Augmentor Flap Research Aircraft  PA1716/5/15/14  February 1969

1 Item

Rolls-Royce Orpheus Vectored-Thrust Engine for the CV-7A Buffalo Augmentor Flap Research Aircraft, Development Programme  PA1716/5/15/15  March 1969

1 Item

Bristol Orpheus Engine: Installation Folder  PA1716/5/15/16  c. April 1955

1 Item

Orpheus B.Or.3 Lightweight Jet Propulsion Engine: Installation Data  PA1716/5/15/17  November 1956

1 Item

Orpheus Licence - India: Recommended Equipment for Aero-Engine Overhaul Factory at Bangalore  PA1716/5/15/18  c. May 1957

1 Item

Contents:
Includes related letter

Orpheus B.Or.12R Engine: Project Study  PA1716/5/15/19  July 1957

1 Item

Article from 'The Aeroplane': The Versatile Orpheus  PA1716/5/15/20  22 November 1957

1 Item

Orpheus Mark 703, Lightweight Turbine Engine: Installation Data  PA1716/5/15/21  April 1958

1 Item

Orpheus Mark 803 Turbojet Engine: General Description  PA1716/5/15/22  April 1959

1 Item

Brochure: Orpheus Lightweight Turbojet  PA1716/5/15/23  June 1959

1 Item

Marine Orpheus 1300: General Description  PA1716/5/15/24  October 1959

1 Item

Orpheus Engines Series 800: Installation Data  PA1716/5/15/25  c. November 1959

1 Item

T.O. NATO 2J-J80302-3, General Description and Installation Data  PA1716/5/15/26  c. 1960s

1 Item

Orpheus Mark 803 Turbojet Engine: General Description  PA1716/5/15/27  c. 1960s

1 Item

Orpheus Series Engine: Provisional Aero-Engine School Course Notes  PA1716/5/15/28  c. 1960s

1 Item

Orpheus Engine Diagrams  PA1716/5/15/29  c. 1960s

1 Item

Engine Handling Notes for Bristol Orpheus 701 (E.C.U. 70101) in Folland GNAT Mk.1  PA1716/5/15/30  c. 1960s

1 Item

Brochure: Orpheus Light-weight turbojet  PA1716/5/15/31  c. 1960s

1 Item

Orpheus engine photographs  PA1716/5/15/32  c. 1960s

154 Items

Orpheus 80506 E.C.U. in Fuji T.1A. Aircraft: Engine Handling Notes  PA1716/5/15/33  May 1961

1 Item

Brochure: Orpheus Lightweight Turbojet  PA1716/5/15/34  September 1961

1 Item

Orpheus Mark 803 Lightweight Turbojet Engine: Performance Data  PA1716/5/15/35  March 1962

1 Item

Orpheus Mark 703 Lightweight Turbojet Engine (4% increased turbine throat area): Performance Data  PA1716/5/15/36  August 1962

1 Item

An Overhaul Base for Orpheus Engines: General Description  PA1716/5/15/37  July 1963

1 Item

Orpheus 7035-10 E.C.U. in Egyptain Aircraft, H.A.300 V.I. Prototype: Engine Handling Notes  PA1716/5/15/38  April 1964

1 Item

Brochure: Orpheus Turbojet  PA1716/5/15/39  May 1965

1 Item

Orpheus Thrust-Boost Engine for the Hawker Siddeley Trident Mark 3B  PA1716/5/15/40  November 1966

1 Item

Orpheus Thrust-Boost Engine for the Hawker Siddeley Andover 748 MF  PA1716/5/15/41  June 1967

1 Item

A New Proposal for the Bristol Orpheus with 5759lb Thrust-Boost for Victor Mk 1 Tanker  PA1716/5/15/42  January 1968

1 Item

Bristol Orpheus Engines M.O.A. Volume 1  PA1716/5/15/43  May 1977

1 Item

Arrangement Drawings: Orpheus B.Or.11 and B.Or.12 Engines  PA1716/5/15/44  1959

1 Item

Arrangement Drawings: Orpheus Mark 703 and Orpheus Mark 70308 and 70309 E.C.U's  PA1716/5/15/45  1961

1 Item

Arrangement Drawings: Orpheus 700 Engine Series  PA1716/5/15/46  1958

1 Item

Arrangement Drawings: Orpheus 70308-9 Engine  PA1716/5/15/47  1957

1 Item

Arrangement Drawings: Orpheus Mark 803 Engine, Orpheus Mark 80302, 803D-11 and 803F-12 E.C.U.  PA1716/5/15/48  1961

1 Item

Arrangement Drawings: Orpheus Mark 701 Engine and Orpheus Mark 70101 E.C.U.  PA1716/5/15/49  1961

1 Item

Arrangement Drawings: Orpheus Mark 10101 Engine  PA1716/5/15/50  1962

1 Item

Arrangement Drawings: Orpheus Mark 100 Engine  PA1716/5/15/51  January 1961

1 Item

Arrangement Drawings: Orpheus 810 Engine  PA1716/5/15/52  1959

1 Item

Arrangement Drawings: Orpheus B.Or.4 Engine  PA1716/5/15/53  1960

1 Item

Arrangement Drawings: Orpheus  PA1716/5/15/54  [n.d.]

Arrangement Drawings: Orpheus  PA1716/5/15/55  [n.d.]

Pegasus Engine  PA1716/5/16  [n.d.]

Project Study: Ducted Fan Engine, B.E.58  PA1716/5/16/1  January 1959

1 Item

Brochure: V/Stol aircraft  PA1716/5/16/2  c. 1960s

1 Item

Contents:
Covering page missing

Brochure: 'Bristol Siddeley BS 53 lift/thrust engine'  PA1716/5/16/3  July 1960

1 Item

'The Aeroplane and Astronautics': Bristol Siddeley BS.53, Civil Ducted Fan  PA1716/5/16/4  12 August 1960

1 Item

Preliminary Data: Bristol Siddeley BS.85/2, Ducted Fan Engine  PA1716/5/16/5  September 1960

1 Item

Volume of Diagrams of NCU9149  PA1716/5/16/6  25 October 1960

1 Item

Engineering and Commercial Considerations: Bristol Siddeley BS.75 for the British Aircraft Corporation Type 107  PA1716/5/16/7  November 1960

1 Item

Design Study: Exhauster System for an Underground Guided Weapon, BS.603  PA1716/5/16/8  March 1962

1 Item

Design Study: Barrel Engines, BS.611  PA1716/5/16/9  February 1963

1 Item

Preliminary Performance: Pegasus Bs Pg 5, Ducted Fan Lift Thrust Engine, Engines for Hawker P1127 Evaluation Squadron  PA1716/5/16/10  February 1963

1 Item

Volume of photographs of Pegasus in Test House 56  PA1716/5/16/11  c. 1960s

Contents:
Includes note detailing contents and 3 related unattached photographs

Report: Pegasus Vectored-Thrust Turbofan  PA1716/5/16/12  October 1971

1 Item

Tyne Engine  PA1716/5/17  [n.d.]

Brochure: Rolls-Royce 360-07, Two Spool-Gas Turbine  PA1716/5/17/1  May 1968

1 Item

Brochure: Adour Mk 871/F405-RR-401 turbofan  PA1716/5/17/2  September 1989

1 Item

Development Programme: Uprated Tyne Engine for Belfast Aircraft  PA1716/5/17/3  December 1964

1 Item

Description and Operation: Fuel Burners, Test Rigs Section  PA1716/5/17/4  24 August 1959

1 Item

Preliminary Design Study: Tyne gearbox and main gearing  PA1716/5/17/5  October 1967

1 Item

Design Feasibility Study for 2MW Turbo-Generating Set with Waste Heat Boiler  PA1716/5/17/6  February 1969

1 Item

Tyne Titanium Compressor Stress Analysis  PA1716/5/17/7  15 May 1968

1 Item

Customer Training Centre Tyne Course Notes  PA1716/5/17/8  1964

1 Item

Customer Training Centre Tyne Turbine Propulsion Course Notes  PA1716/5/17/9  c. 1970s

1 Item

Contract Specification: Tyne RM1C Module, for Netherlands NAvy  PA1716/5/17/10  February 1975

1 Item

General Specification: Marine Tyne Propulsion Module  PA1716/5/17/11  September 1969

1 Item

Brochure: The Marine Turbine Cruise Gas Turbine  PA1716/5/17/12  November 1979

1 Item

General Description: Tyne Marine Gas Turbine Mk 621  PA1716/5/17/13  January 1968

1 Item

Feasibility Study to Investigate Conversion of the Tyne Engine for Naval Marine Use  PA1716/5/17/14  October 1966

1 Item

Development Cost Plan for Tyne Propulsion Engine RM1A  PA1716/5/17/15  September 1969

1 Item

National Gas Turbine Establishment: Naval Marine Wing Note No. 7/67  PA1716/5/17/16  November 1967

1 Item

General Description: Marine Tyne Gas Turbine RB 209 Propulsion Unit  PA1716/5/17/17  March 1969

1 Item

Mandatory Installation Requirements: Marine Tyne RMIC Propulsion Module  PA1716/5/17/18  August 1978

1 Item

Installation Data: Marine Tyne Gas Turbine  PA1716/5/17/19  November 1979

1 Item

General Specification: Marine Tyne Propulsion Module  PA1716/5/17/20  March 1969

1 Item

General Description: Marine Tyne RM1A Gas Turbine  PA1716/5/17/21  January 1970

1 Item

General Description: Marine Tyne RMI Gas Turbine  PA1716/5/17/22  January 1970

1 Item

Summary of Operation: Tyne  PA1716/5/17/23  September 1976 - March 1979

3 Items

Development Cost Plan: Tyne Module Shore Trials in Support of Type 42  PA1716/5/17/24  August 1972

1 Item

Development Cost Plan: for Tyne Propulsion Engines for R.N. Frigate  PA1716/5/17/25  April 1968

1 Item

Development Cost Plan: for the Propulsion Engines for R.N. Frigate  PA1716/5/17/26  March 1969

1 Item

Volume of publicity material relating to Rolls-Royce Tyne  PA1716/5/17/27  1960s - 1980

13 Items

Report: Project 1010, Fixed Shaft Tyne Fo DX/DXG  PA1716/5/17/28  15 July 1968

1 Item

Tyne Stress Calculations  PA1716/5/17/29  1967 - 1971

8 Items

Marine Tyne Engine No. 18 - 1000 hours Marine Environmental Trial Report  PA1716/5/17/30  July 1967 - August 1967

1 volume

Contents:
From the Rolls-Royce Aero Engine Development department; includes photographs of engine parts.

Installation Drawing for Marine Tyne Engines 621 and 621/10  PA1716/5/17/31  22 September 1965

1 item

Contents:
Sheet 1 of 4; large. Also see PA1716/5/17/32.

Drawing for Marine Tyne Engines 621 and 621/10  PA1716/5/17/32  c.1967

1 item

Contents:
Sheet 2 of 4; large. Also see PA1716/5/17/31.

Allison Engine  PA1716/5/18  [n.d.]

Technical Manual: Turboprop Engine USAF Model, T56-A-15  PA1716/5/18/1  June 1968

1 Item

Installation, Operation, Maintenance Instruction Manual: Propeller Brake Assembly Test Stand  PA1716/5/18/2  1 April 1960

1 Item

Operating and Service Instructions for High Speed Balance Machine  PA1716/5/18/3  c. 1960s

1 Item

Aircraft Service Training Manual: Instruction Handbook for T56-A-15 Turboprop Engine  PA1716/5/18/4  1964

1 Item

Allison Propeller Field Maintenance Instructions. Operational Supplement, Technical Manual  PA1716/5/18/5  1960s - 1970s

1 Item

Group Assembly Part List T.O. 2J-T56-44  PA1716/5/18/6  1964

1 Item

Brochure: Allison Industrial/Marine Gas Turbines  PA1716/5/18/7  c. 1977

1 Item

Installation, Operation, Maintenance and Parts: Speed Decreaser Test Stand  PA1716/5/18/8  1 December 1964

1 Item

Test Schedule: Allison T56-A-15 Engine  PA1716/5/18/9  31 May 1966

1 Item

Technical Manual: Dual Gear and Booster Type Fuel Pump  PA1716/5/18/10  10 January 1969

1 Item

Maintenance Manual: Torquemeter Indicating System - Maintenance Practices  PA1716/5/18/11  1960s

1 Item

Supplement Technical Manual: General Block Test Instructions  PA1716/5/18/12  6 December 1965

1 Item

Supplement Technical Manual: General Block Test Instructions  PA1716/5/18/13  1 April 1967

1 Item

Technical Manual: General Block Test Instructions  PA1716/5/18/14  19 May 1971

2 Items

Instructions to Test Crews: Quality Control and Inspection, Structure and Procedures  PA1716/5/18/15  1964 - 1977

1 Item

Proposals to Provide Defects Investigation Facility for Allison T. 56-A-15 Turboprop Engine  PA1716/5/18/16  June 1966

1 Item

Report on the Visit of Mr. Hazen of Allisons to Mr. Lindsey  PA1716/5/18/17  19 September 1955

1 Item

Report on Allison T56-A-15 Production Quality Test Accessory Loading  PA1716/5/18/18  28 July 1971

1 Item

Report on Allison Filter Testing  PA1716/5/18/19  26 June 1972

1 Item

Report on Allison T.56-15 Torquemeter Shaft Calibration  PA1716/5/18/20  5 July 1971

1 Item

Technical Manual for Allison Engine, with attached diagrams  PA1716/5/18/21  1950s

1 Item

Proposals to Overhaul Allison T56-A-15 Turboprop Engine in No.4 Shop Ansty  PA1716/5/18/22  March 1966

1 Item

General Description: Allison T.56-A-15 Engine  PA1716/5/18/23  1960 - 1970

1 Item

Contents:
Includes BSE Report (31 August 1966), notes from change over from Proteus to Allison testing, memo on oil priming procedure for Allison engines

54H60 Special Support Equipment for Hamilton Standard Hydromatic Propellers  PA1716/5/18/24  1965

1 Item

File of T56-A-15 Technical Notes and Drawings  PA1716/5/18/25  1964

1 Volume

File of publicity material for Allison Engine  PA1716/5/18/26  1960s - 1970s

11 Items

Allison Gas Turbines Specifications  PA1716/5/18/27  March 1978

1 file

Orion Engine  PA1716/5/19  [n.d.]

General Description: Orion B.On.1 Propeller Turbine Engine  PA1716/5/19/1  July 1956

1 Item

Orenda Engine  PA1716/5/20  [n.d.]

General Description: Orenda Industrial Gas Turbine OT-2 Series  PA1716/5/20/1  January 1965

1 Item

General Description: Orenda Industrial Gas Turbine OT-3 Series  PA1716/5/20/2  May 1964

1 Item

General Description: Orenda Industrial Gas Turbine OT-5 Series  PA1716/5/20/3  February 1965

1 Item

Gas Turbine (General)  PA1716/5/21  [n.d.]

Turbine Design  PA1716/5/21/1  [n.d.]

Letter from Stanley Belsky and Richard Facciola to R.G. Lommel regarding stresses of XT49W1 Turbine Rotor Blades  PA1716/5/21/1/1  1 November 1954

1 Item

National Gas Turbine Establishment: The Constitution, Microstructure and Mechanical Properties of Some Experimental Nickel Cast Superalloys, by J.E. Restall  PA1716/5/21/1/2  June 1974

1 Item

National Gas Turbine Establishment: Metallurgical Observations on the Factors Influencing the Mechanical Behaviour of Some Experimental Nickel Cast Superalloys by J.E. Restall  PA1716/5/21/1/3  June 1974

1 Item

National Gas Turbine Establishment: A Note on the Manufacture of a Two Stage Turbine Rotor from a Solid Billet  PA1716/5/21/1/4  c. 1974

1 Item

Contents:
Includes photographs

Rolls-Royce: Cooled Turbine Technology  PA1716/5/21/1/5  c. 1970s

1 Item

Report on the Design Study for Machining the entire Swept Surface of Blades for Aero Gas Turbine Engines  PA1716/5/21/1/6  February 1959

1 Item

Brochure summarising special purpose equipment designed and manufactured by Armstrong Siddeley for the production of development blades  PA1716/5/21/1/7  c. 1970s

1 Item

The Association of Engineering and Shipbuilding Draughtsmen: An Introduction to Gas Turbines, by William L. Gross  PA1716/5/21/1/8  c. 1950

1 Item

Prints concerning turbine design  PA1716/5/21/1/9  c. 1960s

43 Items

Turbine Analysis  PA1716/5/21/2  1951 - 1955

File 1: Engine Analysis  PA1716/5/21/2/1  7 January 1955 - 27 May 1955

19 Items

File 2: Development and Research Expedition  PA1716/5/21/2/2  11 October 1951 - 1 April 1953

31 Items

File 3: Analysis Updates  PA1716/5/21/2/3  14 October 1955 - 30 December 1955

11 Items

Notes for Tenderers on Earthquake Resistance for Gas Turbines  PA1716/5/21/2/4  c.1972

1 item

Contents:
Copy.

Auxiliary Power Units  PA1716/5/21/3  [n.d.]

Project Design Study: Auxiliary Power Unit for High Altitude Aircraft  PA1716/5/21/3/1  September 1952

1 Item

General Description: Auxiliary Power Units  PA1716/5/21/3/2  1966

1 Item

Brochure: Gas Generator for Starting Naval Aircraft  PA1716/5/21/3/3  October 1957

1 Item

General Description: Auxiliary Equipment  PA1716/5/21/3/4  1960

1 Item

Brochure: Auxiliary power gas turbines combination unit model G.T.C.P. 100  PA1716/5/21/3/5  c. 1964

1 Item

Brochure: Auxiliary power gas turbines and air turbine starters  PA1716/5/21/3/6  c. 1963

1 Item

Brochure: Auxiliary Gas Turbines  PA1716/5/21/3/7  c. 1965

1 Item

Brochure: Gas Turbine Compressor Shaft Power Unit, Model GTP.250-2  PA1716/5/21/3/8  c. 1955

1 Item

Brochure: Gas Turbine Compressor and Shaft Power Unit, Model GTCP 85  PA1716/5/21/3/9  c. 1956

1 Item

Brochure: Gas Turbine Power Unit, Model GTP 30-1  PA1716/5/21/3/10  c. 1957

1 Item

Brochure: The Rover 1S/60, Single Shaft Gas Turbine  PA1716/5/21/3/11  c. 1958

1 Item

Brochure: Auxiliary Powerplants  PA1716/5/21/3/12  c. 1960

1 Item

Brochure: Signmund Rover, Gas Turbine Driven Fire Pump  PA1716/5/21/3/13  c. 1959

2 Items

Contents:
With related clipping

Brochure: Auxiliary Power Unit  PA1716/5/21/3/14  c. 1962

1 Item

Operation and Service Instructions: Gas Turbine Compressor Unit  PA1716/5/21/3/15  15 April 1957

1 Item

Adour Engine  PA1716/5/22  [n.d.]

Brochure: Visit of the Jaguar Management Committee to Rolls-Royce  PA1716/5/22/1  1975

1 Item

Brochure: The Rolls-Royce Turbomeca Adour  PA1716/5/22/2  August 1970 - September 1970

2 Items

Contents:
Includes related information bulletin

Brochure: Adour Mk871/F405-RR-401 turbofan  PA1716/5/22/3  September 1989

1 Item

Brochure: Adour Mk881  PA1716/5/22/4  February 1991

1 Item

Brochure: Adour Commonality  PA1716/5/22/5  October 1982

1 Item

Brochure: Rolls-Royce Turbomeca Adour Training  PA1716/5/22/6  July 1980

1 Item

Brochure: Adour/F405 Turbofan  PA1716/5/22/7  April 1992

1 Item

Leaflet: Adour Progress  PA1716/5/22/8  September 1980

1 Item

Leaflet: Adour  PA1716/5/22/9  1992

1 Item

Adour Engine: In Service Problems  PA1716/5/22/10  February 1975

1 Item

RB 199 Engine  PA1716/5/23  [n.d.]

Familiarisation Course: Turbo-Union RB 199  PA1716/5/23/1  1980s

2 Items

General Description: RB 199 Reheated Turbofan  PA1716/5/23/2  October 1983

1 Item

Brochure: RB 199 for MRCA  PA1716/5/23/3  c. 1970s

1 Item

Brochure: Turbo-Union RB199 Military Reheated Turbofan  PA1716/5/23/4  1976 - 1980

6 Items

National Engineering Laboratory, East Kilbride  PA1716/5/24  [n.d.]

Brochure: Aero engine overhaul and services, Rolls-Royce (1971) Limited, East Kilbride  PA1716/5/24/1  c. 1970s

1 Item

Brochure of Special Purpose Machines and Equipment for the production of Compressor and Turbine Blades compiled by the G.T.C.C. Manufacturing Sub-Committee's Blade Panel  PA1716/5/25  June 1956

1 item

Contents:
Copy No. 8; sections submitted by Armstrong Siddeley, Bristol Aero-Engines Limited, De-Havilland Engine Company Limited, D. Napier & Son Limited and Rolls Royce Limited; includes photographs.

Confidential Report - 'The Application of the Closed Cycle in a Heavyweight Torpedo'  PA1716/5/26  July 1970

1 item

Contents:
Rolls-Royce Limited Industrial and Marine Gas Turbine Division

Bristol Siddeley Industrial Division Ten Year Forecast  PA1716/5/27  April 1966 - March 1976

1 item

Contents:
Company Confidential Report

Rolls-Royce Limited Industrial and Marine Gas Turbine Division Five Year Sales Forecast  PA1716/5/28  12 July 1968

1 item

Rolls-Royce R.B. 141 Rating Engine Estimated Performance Data and Installation Notes  PA1716/5/29  June 1958

2 items

Contents:
Printed report; also includes 'Rolls-Royce RB 401 Advanced Turbofan for Business Aircraft in the 1980s' booklet .

Rolls-Royce R.B. 109 Engine Initial Project Performance Data and Installation Notes  PA1716/5/30  June 1953

1 item

Contents:
Printed report.

The Application of the Gas Turbine to Aircraft Propulsion  PA1716/5/31  March 1946

1 item

Contents:
By Dr S. G. Hooker

Cooper Energy Services RT62 Two-Stage Power Turbine Report  PA1716/5/32  December 1982

1 item

Contents:
Addenda 1 and 2 of PTR 111; Rolls-Royce Limited.-

Material relating to Fuel for Gas fuelled eqipment  PA1716/5/33  c.1981

1 file

Contents:
Includes Rolls-Royce Fuel Requirements Guideance Paper and photocopies of newspaper cuttings concerning consumern habbits and international fuel situation.

Spey Gas Generator  PA1716/5/34  [n.d.]

The Industrial Spey Condition Monitoring Report  PA1716/5/34/1  July 1976

1 item

Contents:
Rolls-Royce Industrial and Marine Division.

General Specification SM1A Marine Propulsion Module  PA1716/5/34/2  October 1979

1 item

Contents:
Rolls-Royce Limited Industrial and Marine Division; [comprises a Spey 1903 gas generator].

Rolls-Royce SM series gas turbines for marine propulsion  PA1716/5/34/3  September 1981

1 item

Contents:
Rolls-Royce Limited; details Marine Spey Propulsion Units; printed report.

Spey R.Sp.1 Engine Performance Specification and Installation Notes  PA1716/5/34/4  December 1961

1 item

Contents:
Issue 3; Rolls-Royce Limited.

Marine Spey SM1A propulsion Module - mandatory installation requirements  PA1716/5/34/5  August 1984

1 item

Contents:
Issue 2; Rolls-Royce Limited; printed report.

SM1A Marine Spey - Machinery Options for Frigates  PA1716/5/34/6  February 1979

1 item

Contents:
Rolls-Royce Limited; printed report.

Industrial and Marine Spey Update Brochure  PA1716/5/34/7  June 1981

1 item

Contents:
Rolls-Royce Limited.

Rolls-Royce Spey Power for the Bac One-Eleven  PA1716/5/34/8  August 1968

1 item

Contents:
Publication.

Rolls-Royce Spey Marine Propulsion Gas Turbine  PA1716/5/34/9  September 1985

1 item

Contents:
Publication.

Printed Material concerning Spey  PA1716/5/34/10  c.1951 - c.1977

1 file

Contents:
Inclueds material from the Hawker Siddeley Company, Japan Press Exchange Limited, Diesel Engineering magazine, The Naval Architect magazine, Flight magazine, and Rolls-Royce.

Spey Industrial Engines Installation Brochure  PA1716/5/34/11  December 1974

1 file

Contents:
Rolls-Royce (1971) Limited, Industrial and Marine Division

Spey Mk.512 Engine - Perfomance Specification and Installation Notes  PA1716/5/34/12  August 1968

1 file

Contents:
Rolls-Royce Limited, Industrial and Marine Division

Product Support - Product Assurance Manual  PA1716/5/35  June 1979

1 item

Contents:
Volume 1 - Organisation and Policy; Rolls-Royce Limited Aero Division, Bristol.

Turbine Engine and Power Plant Design Materials  PA1716/5/36  1950s

1 item

Contents:
Specifications issued by Bristol Aero-Engines Limited.

Air Registration Board Notices  PA1716/5/37  1964 - 1967

1 file

Contents:
Air Registration Board, Brabazon House, Redhill, Surrey.

General Requirements for the Overhaul of Gas Turbine Aero-Engines - Engine Change Units, Engine Modules and Jet Pipes  PA1716/5/38  1968 - 1975

1 file

Contents:
Ministry of Technology Engine Research and Development Division.

Drawing Number Registers  PA1716/5/39  c.1960s - c.1970s

4 items

Helium Gas Turbine Plant for Gas Cooled Reactors  PA1716/5/40  November 1967

1 item

Contents:
Company Confidential Project Study Report, Rolls-Royce Limited, Coventry.

Proposal for Gas Tyrbine HTR  PA1716/5/41  May 1969

1 item

Contents:
Report from the Nuclear Power Group Limited, Rolls-Royce Limited and Heyrolle Parsons Limited.

The Case for Closed-Cycle Gas Turbines with the High Temperature Helium-Cooled Nuclear Reactor  PA1716/5/42  November 1974

1 item

Contents:
Company Confidential Report from Rolls-Royce (1971) Limited, London.

Guide to the AVRO Single-Engine Advanced Trainer aircraft  PA1716/5/43  c.1960s

1 item

Contents:
Considers the aircraft in relation to the Rolls-Royce 1000HP turbine engine and also to the Bristol Perseus Engine.

Civil 'A' Nos  PA1716/5/44  c.1969

1 file

Contents:
Gives list of 'A' numbers, a comment against each one and a signature.

Internal Drawings Register  PA1716/5/45  c.1960s

3 pp.

Contents:
Gives details of reference number, part number, description, size and remarks.

Drawing Register Books Index  PA1716/5/46  c.1960

3 pp.

Contents:
Gives details of Book reference number, entry date and product description.

Part No. Registers  PA1716/5/47  [n.d.]

Part No. Register  PA1716/5/47/1  [n.d.]

1 volume

Contents:
P.E. 1 to P.E. 3259 and I.T. 1 to I.T. 1230.

Part No. Register  PA1716/5/47/2  c.1930s

1 volume

Part No. Register  PA1716/5/47/3  c.1939 - c.1945

1 volume

Unified Threads ?Register  PA1716/5/48  1950-1963

1 volume

Contents:
From Bristol Siddeley Engines Ltd, Coventry.

Compendium of Design and Development Information  PA1716/5/49  September 1954

1 file

Contents:
Armstrong Siddeley Motors Limited, Coventry, England.

Interim Report on Bending Fatiue Tests on Gear Teeth  PA1716/5/50  c.1960s

1 file

Contents:
Armstrong Siddeley Motors Limited Mechanical Engineering Department Research Report; includes photographs.

Armstrong Siddeley Motors Gas Turbine Production Order Book  PA1716/5/51  November 1953 - June 1954

1 file

Cost Analysis of the Development and Research Programme for the first 22 Weeks, April 1st to August 30th, of the current year 1950/1951  PA1716/5/52  2 October 1950

6 pp.

Contents:
Report; ?Armstrong Siddeley Motors Limited.

Cost Analysis of the Development and Research Programme for the first 30 weeks, April 1st to October 25th of the current year 1950/1951  PA1716/5/53  12 December 1950

6 pp.

Contents:
Report; ?Armstrong Siddeley Motors Ltd.

Draft Sales Plan for submission to the Ministry of Supply  PA1716/5/54  18 January 1952

8 pp.

Contents:
Includes covering letter.

Serration Root Index and Photographs  PA1716/5/55  c.1960

2 items

Drawing for First Rotor Blade  PA1716/5/56  1973

1 item

Contents:
Copy

Correspondence concerning visit of Mr E. Hawthorne and work on nuclear reactors  PA1716/5/57  1955

2 items

Contents:
Confidential / Secret.

Reports on Gas Turbine Engines and Aircraft  PA1716/5/58  1958 - 1959

8 items

Contents:
Includes reports on Viper, Sapphire, Lucas, Victor and Mamba; Photocopies.

Letter from Peter Geliot to Dear Mr Harvey-Bailey  PA1716/5/59  1 October 1993

1 item

Contents:
Concerns background information of the mutual assistance rendered between Rolls-Royce and Armstrong Siddeley when the Avon and Sapphite both ran into troubles.

Armstrong Siddeley Gas Turbines  PA1716/5/60  c.1960s

6 pp.

Contents:
Photocopied article from 'Flight' publication.

An Introduction to Gas Turbines  PA1716/5/61  1949 - 1950

1 item

Contents:
Booklet from The Association of Engineering and Shipbuilding Draftsmen; photocopy.

Reports on Icing Tests  PA1716/5/62  1956 - 1962

3 files

Contents:
On Bristol Siddeley Engines at N.A.E. Ottawa, Canada.

Report on Icing Tests  PA1716/5/62/1  1957 - 1957

1 file

Contents:
On Bristol Siddeley Engines at N.A.E. Ottawa, Canada; Turbine Test Department.

Report on Icing Tests  PA1716/5/62/2  1958 - 1959

1 file

Contents:
On Bristol Siddeley Engines at N.A.E. Ottawa, Canada.

Report on Icing Tests  PA1716/5/62/3  1961 - 1962

1 file

Contents:
On Bristol Siddeley Engines at N.A.E. Ottawa, Canada.

Laboratory Reports  PA1716/5/63  1952

1 file

Contents:
Armstrong Siddeley Motors Ltd.

Proposed Research Programme for year 1953 / 1954  PA1716/5/64  c.1953

6 pp.

Contents:
Armstrong Siddeley Motors Ltd.

Test Results for Turbine Blade Materials  PA1716/5/65  c.1980s

1 file

Contents:
Graphs.

Diagram of Hydr. Torque Converter  PA1716/5/66  1956 - 1966

2 items

Contents:
Longitudinal section and Cross Section

Nuclear Gas Turbines  PA1716/5/67  [n.d.]

The Application of Gas-Turbines to Reactor Systems  PA1716/5/67/1  c.1965

1 item

Contents:
Report from Rolls-Royce.

High Temperature Irradiation Facility DIDO.12.HRG.2.DUCT  PA1716/5/67/2  June 1958

1 item

Contents:
Report issued by Bristol Siddeley Engines Limited.

Integrated Nuclear Gas Turbines  PA1716/5/67/3  May 1968

1 item

Contents:
Rolls-Royce Industrial and Marine Gas Turbine Division; Paper to be presented to the E.N.E.A. Symposium on the Technology of Integrated Primary Circuits for Power Reactors, Paris.

Reactor Gas Turbines - Advanced Project Group Reports  PA1716/5/67/4  July 1968 - December 1968

1 file

Contents:
Rolls-Royce Limited.

Nuclear Gas Turbines - Advanced Project Group Reports  PA1716/5/67/5  December 1968 - July 1969

1 file

Contents:
Rolls-Royce Limited.

An Interim Review of the Relative Merits of CO2 and Helium Gas Turbine Closed-Cycle Systems Applied to H.T. Reactors  PA1716/5/67/6  September 1968

1 item

Contents:
Central Electricity Generating Board, Generation Design Departrment, Station Plant Design Branch.

Nuclear Gas Turbine Project Group Reports  PA1716/5/67/7  May 1969 - June 1969

1 file

Contents:
Rolls-Royce Limited, Industrial and Marine Gas Turbine Division.

Direct Cycle Nuclear Power Stations with High Temperature Helium-Cooled Rectors and Gas Turbines  PA1716/5/67/8  October 1969

1 item

Contents:
Summary of the Rolls-Royce Presentation to the HTR-GT Seminar; confidential.

The Future of Nuclear Powered Ships  PA1716/5/67/9  December 1965

1 item

Contents:
Proceedings of the Joint Symposium of The British Nuclear Energy Society, The British Nuclear Forum, The Joint Panel on Nuclear Marine Propulsion; printed.

Turbomachinery  PA1716/5/67/10  May 1965

1 item

Contents:
Report by J. B. Holliday and J. G. Keenan; presented at the Colloquium on Nuclear Gas Turbine Power Plant.

H.T.R. / Gas Turbine Study  PA1716/5/67/11  13 September 1968

1 item

Contents:
Status report from D. E. Williams, Advanced Projects Group, Rolls-Royce Limited, Industrial and Marine Gas Turbine Division.

Report of Meetings of Gulf General Atomic Inc. and Rolls-Royce Ltd  PA1716/5/67/12  September 1968

1 item

Contents:
Report No.5; confidential.

Proposed Development of Nuclear Gas Reactor Components at A.S.M. - R.C.D. Report No. 1  PA1716/5/67/13  November 1955

1 item

Contents:
From A.V. Parker, Mech. Engr. Dept., ?Armstrong Siddeley Motors Limited.

Naval Marine Wing Note No. 20/69  PA1716/5/68  October 1969

1 item

Contents:
Restricted report of the sea salt in air sampling trials carried out in HMS Exmouth June 1969; Ministry of Technology.

Naval Marine Wing Note No. 21/69  PA1716/5/69  November 1969

1 item

Contents:
Restricted report of the sea salt in air sampling trials carried out in HMS Exmouth June 1969; Ministry of Technology.

Gas Turbines in the 1980's  PA1716/5/70  c.1977

1 item

Contents:
Presented at The Royal Navy Equipment Exhibition.

General Material relating to Gas Turbines  PA1716/5/71  1969 - 1990

1 file

Contents:
Includes newspaper clippings, press releases and some in-house publications.

Small Gas Turbine Engines - The State of the Art in the World Today  PA1716/5/72  c.1955

1 item

Contents:
Armstrong Siddeley Motors Limited

Advanced Engineering - Archived Drawings  PA1716/5/73  November 1988

1 item

Contents:
List; ?Rolls-Royce.

Proposal for a New 7 1/2 MW Vapour Turbine  PA1716/5/74  c.1966

1 item

Contents:
Bristol Siddeley Engines Limited, Advanced Projects Group.

Rolls-Royce SM1A & SM2B Gas Turbines for Marine Propulsion  PA1716/5/75  July 1977

1 item

Contents:
Rolls-Royce Limited, Industrial and Marine Division.

Specification and Design of a Shore Trials Facility for C.A.H. Machinery  PA1716/5/76  c.1971

1 item

Contents:
Rolls-Royce Limited, Industrial and Marine Division.

Guidance Notes for the Design of Gas Turbine Intakes and Exhausts for Ships  PA1716/5/77  1978

1 item

Contents:
Rolls-Royce Limited, Industrial and Marine Division.

Fuel  PA1716/5/78  c.1951 - 1977

7 items

Contents:
Reports and articles on the use and development of fuel.

Fluidised Bed Gas Generation Presentation Overhead Projections and Photographs  PA1716/5/79  c.1978

1 file

Contents:
Rolls-Royce LImited.

Rolls-Royce Range of Gas Turbine Generating Sets  PA1716/5/80  14 November 1975

1 item

Contents:
Report.

Glacier Bearings in Gas Turbine Generating Sets  PA1716/5/81  1970

1 item

Contents:
Report by The Glacier Meta; Company Ltd, Middlesex.

Rolls-Royce Gas Turbines for Electrical Generation and Gas and Oil Pumping  PA1716/5/82  1977

1 item

'A New Look in Gas Transmission'  PA1716/5/83  October 1966

1 item

Contents:
An address to the Industrial Contractors Association of Canada.

2,500 H.P. Recuperative Gas Turbine  PA1716/5/84  October 1965

1 item

Contents:
Preliminary proposals for a 1.8 MW Total Energy Plant; Bristol Siddeley Engines Limited, Advanced Projects Group.

Free Power Turbine Dart Engine for Rail Traction - Development Plan  PA1716/5/85  May 1968

1 item

Contents:
Rolls-Royce Limited, Industrial and Marine Gas Turbine Division.

General Description of Dart Free Power Turbine Unit for Railway Traction  PA1716/5/86  c.1968

1 item

Contents:
Rolls-Royce Limited, Industrial and Marine Gas Turbine Division.

Proposals for Hih Temperature Turbines  PA1716/5/87  2 January 1969

1 item

Contents:
Rolls-Royce Limited, Industrial and Marine Gas Turbine Division.

Gas Turbine Power for Railways Report  PA1716/5/88  1967

1 item

Contents:
Rolls-Royce Limited, Derby.

Correction Chart for Gas Turbine Engines  PA1716/5/89  March 1952

1 item

Contents:
Rolls-Royce Limited.

Bristol Siddeley Centaur Marine Gas Turbine  PA1716/5/90  1966

1 item

Contents:
Company Confidential report; Bristol Siddeley Engines Limted, Advancerd Projects Group.

Centaur Marine Gas Turbine  PA1716/5/91  November 1966

1 item

Contents:
Company Confidential report; Bristol Siddeley Engines Limted, Project Study.

A Survey of Gas Generator Prospects  PA1716/5/92  November 1957

1 item

Contents:
Armstrong Siddeley Motors Limited.

Super Sonic Nozzles for Gas Turbines  PA1716/5/93  12 January 1947

1 item

Contents:
Report from Aero Dynamics section of the Experimental Department, Armstrong Siddeley Motors Limited.

Operation of Gas Turbines on Liquid Hydrogen  PA1716/5/94  1981

1 item

Contents:
Report from F. A. Hewitt, Advanced Research Laboratory, Rolls-Royce Limited.

Windage Losses of Small Turbines  PA1716/5/95  22 September 1953

1 item

Contents:
Printed report by J.W. Hoyt and C.D. Runge, Underwater Ordnance Department, U.S. Naval Ordnance Test Station.

Dimensional Analysis as applied to the Gas Turbine  PA1716/5/96  12 June 1950

1 item

Contents:
Report by M. Mutz, ?Armstrong Siddeley Motors Ltd.

Gas Turbunes for ACVs - past, present and future  PA1716/5/97  19 November 1964

1 item

Contents:
Article by G.G. Connor, Bristol Siddeley Engines Limited; Reprinted from 'Flight - International Supplement' magazine.

List of British and Canadian Gas Turbine Aero Engines  PA1716/5/100  10 May 1950

5 pp.

Contents:
From D. Lambert, ?Armstrong Siddeley Motors Ltd

Photographs and Drawings of Camm Engines, Propulsion Engines, Friction Drive and Cyclye Systems  PA1716/5/101  c.1967

1 file

Estimation of Aircraft Intake Losses at Take-Off and Subsonic Flight  PA1716/5/102  14 September 1959

1 item

Contents:
Report from Bristol Siddeley Engines Ltd, Aerodynamics Dept.

The Performance of a Small Axial Flow Turbine  PA1716/5/103  15 June 1962

1 item

Contents:
Report from Bristol Siddeley Engines Ltd, Aerodynamics Dept.

A Graphical Method of Obtaining Turbine Blade Loss Coefficients  PA1716/5/104  15 Aoril 1959

1 item

Contents:
Report from Bristol Siddeley Engines Ltd, Aerodynamics Dept.

The Performance of a Small Axial Flow Turbine  PA1716/5/105  10 August 1962

1 item

Contents:
Confidential report from Bristol Siddeley Engines Ltd, Aerodynamics Dept.

The Effect of Pitch Chord Ratio on the Perfoamnce of a Single Stage Turbine  PA1716/5/106  14 January 1954

1 item

Contents:
Report from Armstrong Siddeley Motors Ltd, Aerodynamics Dept.

Feasibility Study - Model Centripetal Turbine Tests  PA1716/5/107  c.1966

1 file

Contents:
Report from Bristol Siddeley Engines Ltd, Aerodynamics Dept.

10 Stage Research Compressor Profile Producer  PA1716/5/108  22 November 1960

1 file

Contents:
Report from Bristol Siddeley Engines Ltd, Aerodynamics Dept.

The S.R.D.A.S. Brochure  PA1716/5/109  c.1969 - 1972

1 file

Contents:
Instructional Manual of the Service Recording and Data Analysis System

The S.R.D.A.S. Coding Manual  PA1716/5/110  c.1968 - 1972

1 file

Contents:
Instructional Manual of the Service Recording and Data Analysis System

Gas Turbine Reduction Gear Data Spur Gears  PA1716/5/111  1961

1 p.

Contents:
Copy.

Accessories  PA1716/5/112  [n.d.]

Lucas Brochures  PA1716/5/112/1  1946 - c.1950

2 items

Contents:
Joseph Lucas Ltd, Birmingham.

Smiths Industries Ltd Aviation Division Reports  PA1716/5/112/2  1963 - 1974

5 items

The Plessey Company Limited Dynamics Group  PA1716/5/112/3  1967

1 item

Contents:
Overhaul Manual for 28V D.C. Motor.

Dowty Equipment Limited Engine Division  PA1716/5/112/4  1950 - 1963

3 items

Contents:
Cheltenham.

Rotol Airscrews Ltd  PA1716/5/112/5  1941 - 1944

4 items

Contents:
Brochures and procedures.

Rotax Limited  PA1716/5/112/6  1952 - 1953

3 items

Contents:
Brochures; Rotax Limited, London.

Curtis Electrically Operated Airscrews  PA1716/5/112/7  November 1941

1 item

Contents:
Notes on Installation, Operation and Maintenance.

Miscellaneous papers concerning accessories  PA1716/5/112/8  .c1950 - c.1960

1 file

Contents:
Drawings and correspondence.

Blackburn Gas Turbines  PA1716/5/113  c.1960

1 item

Contents:
Blackburn Engines Ltd brochure.

Engine Drawings  PA1716/5/114  c.1960s

5 items

Contents:
Mixed drawings of engines

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