Rolls-Royce Olympus
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Rolls-Royce Olympus

Olympus
Bristol Olympus.jpg
Preserved Bristol Siddeley Olympus Mk 301 Engine Change Unit (ECU) complete with ancillaries and bulkheads.
Type Turbojet
United Kingdom
Manufacturer Bristol Aero Engines
Bristol Siddeley Engines Limited
Rolls-Royce Bristol Engine Division
First run 1950
Avro Vulcan
BAC TSR-2
Rolls-Royce/Snecma Olympus 593
Rolls-Royce Marine Olympus

The Rolls-Royce Olympus (originally the Bristol B.E.10 Olympus) was the world's first two-spool axial-flow turbojet aircraft engine design,[1][2] dating from November 1946,[3][4] although not the first to run or enter service. It was originally developed and produced by Bristol Aero Engines. First running in 1950,[5] its initial use was as the powerplant of the Avro Vulcan V bomber. The design was further developed for supersonic performance as part of the BAC TSR-2 programme. Later it saw production as the Rolls-Royce/Snecma Olympus 593, the powerplant for Concorde SST. Versions of the engine were licensed to Curtiss-Wright in the US as the TJ-32 or J67 (military designation) and the TJ-38 'Zephyr'. The Olympus was also developed with success as marine and industrial gas turbines.

Bristol Aero Engines (formerly Bristol Engine Company) merged with Armstrong Siddeley Motors in 1959 to form Bristol Siddeley Engines Limited (BSEL), which in turn was taken over by Rolls-Royce in 1966.

As of 2018, the Olympus remains in service as both a marine and industrial gas turbine.

Background

Origins

At the end of World War II, the Bristol Engine Company's major effort was the development of the Hercules and Centaurus radial piston engines. By the end of 1946, the company had only 10 hours of turbojet experience with a small experimental engine called the Phoebus which was the gas generator or core of the Proteus turboprop then in development.[6] In early 1947, the parent Bristol Aeroplane Company submitted a proposal for a medium-range bomber to the same specification B.35/46 which led to the Avro Vulcan and Handley Page Victor. The Bristol design was the Type 172 and was to be powered by four or six Bristol engines of 9,000 lbf (40 kN) thrust[7] to the Ministry engine specification TE.1/46.

The thrust required of the new engine, then designated B.E.10 (later Olympus), would initially be 9,000 lbf (40 kN) with growth potential to 12,000 lbf (53 kN). The pressure ratio would be an unheard of 9:1.[8] To achieve this, the initial design used a low-pressure (LP) axial compressor and a high-pressure (HP) centrifugal compressor, each being driven by its own single-stage turbine. This two-spool design eliminated the need for features such as variable inlet guide vanes (Avon, J79), inlet ramps (J65), variable stators (J79) or compressor bleed (Avon) which were required on single spool compressors with pressure ratios above about 6:1. Without these features an engine could not be started nor run at low speeds without destructive blade vibrations. Nor could they accelerate to high speeds with fast acceleration times ("spool up") without surge.[9] The design was progressively modified and the centrifugal HP compressor was replaced by an axial HP compressor. This reduced the diameter of the new engine to the design specification of 40 in (100 cm). The Bristol Type 172 was cancelled though development continued for the Avro Vulcan and other projects.[10]

Initial development

Gas-flow diagram of Olympus Mk 101

The first engine, its development designation being BOl.1 (Bristol Olympus 1), had six LP compressor stages and eight HP stages, each driven by a single-stage turbine. The combustion system was novel in that ten connected flame tubes were housed within a cannular system: a hybrid of separate flame cans and a true annular system. Separate combustion cans would have exceeded the diameter beyond the design limit, and a true annular system was considered too advanced.[11]

In 1950, Dr (later Sir) Stanley Hooker was appointed as Chief Engineer of Bristol Aero Engines.[11]

The BOl.1 first ran on 16 May 1950 and was designed to produce 9,140 lbf (40.7 kN) thrust and to be free from destructive rotating stall on start up to idle speed and to be free from surging on fast accelerations to maximum thrust. The engine started without a problem and Hooker, supervising the first test run and displaying the confidence he had in the design, slammed the throttle to give a surge-free acceleration to maximum power.[12] The thrustmeter showed 10,000 lbf (44 kN).[13] The next development was the BOl.1/2 which produced 9,500 lbf (42 kN) thrust in December 1950. Examples of the similar BOl.1/2A were constructed for US manufacturer Curtiss-Wright which had bought a licence for developing the engine as the TJ-32 or J67 for the projected F-102. The somewhat revised BOl.1/2B, ran in December 1951 producing 9,750 lbf (43.4 kN) thrust.[14] The engine was by now ready for air testing and the first flight engines, designated Olympus Mk 99, were fitted into a Canberra WD952 which first flew with these engines derated to 8,000 lbf (36 kN) thrust in August 1952. In May 1953, this aircraft reached a world record altitude of 63,668 ft (19,406 m).[15] (Fitted with more powerful Mk 102 engines, the Canberra increased the record to 65,876 ft (20,079 m) in August 1955.[16]) The first production Olympus, the Mk 101, entered service in late 1952 at a rated thrust of 11,000 lb, a weight of 3,650 lb, and with a TBO of 250 hours.[17]

Variants

The Olympus was developed extensively throughout its production run, the many variants can be described as belonging to four main groups.

Initial non-afterburning variants were designed and produced by Bristol Aero Engines and Bristol Siddeley and powered the Avro Vulcan. These engines were further developed by Rolls-Royce Limited.

The first afterburning variant, the Bristol Siddeley Olympus Mk 320, powered the cancelled BAC TSR-2 strike aircraft. A further afterburning variant was the Rolls-Royce/Snecma Olympus 593, jointly developed to power Concorde in the 1960s.

The American Curtiss-Wright company tested a license-developed version known as the J67 and a turboprop designated TJ-38 Zephyr. Neither design was produced.

Further derivatives of the Olympus were produced for ship propulsion and land-based power generation.

Applications

Proposed aircraft applications

Over the years, the Olympus was proposed for numerous other applications including:

  • C104 which led to the C105 Avro Arrow: BOl.3"[18]
  • Avro 718: BOl.3[19] The Type 718 was a military transport aircraft with up to 110 seats.[20]
  • Avro 739 to OR339 (the requirement that culminated in TSR2): BOl.21R[19][21]
  • Avro 740: 3 x Mk 551[19]
  • Avro 750: 2 x Mk 551[19]
  • Avro Vulcan Phase 6 (B3): BOl.23, a development of the Mk 301.[21] Different engine configurations, BOl.21, BOl.21/2 and BOl.23, with either reheat or an aft fan, were proposed for this aircraft to provide the required increase in take-off thrust.[22][23]
  • Bristol T172: B.E.10[21]
  • Bristol T177[21]
  • Bristol T180[21]
  • Bristol T198: Mk 591. Early supersonic airliner design (132 seats). The engine was a civilianised BOl.22R.[21]
  • Bristol T201: Mk 551[21]
  • Bristol T202[21]
  • Bristol T204 to OR339: BOl.22SR (simplified reheat)[21]
  • Bristol T205: Mark 551[21]
  • Bristol T213[21]
  • Bristol T223: Mk 593. Later supersonic airliner design (100 seats). Engine as Mk 591 with zero stage LP compressor and cooled HP turbine.[21]
  • de Havilland design to OR339: BOl.14R, BOl.15R. Developed from BOl.6R.[21]
  • Handley Page HP98: Pathfinder variant of Victor.[21]
  • Handley Page Victor B1: Mk 104[21]
  • Handley Page Victor Phase 3[21]
  • Handley Page HP107[21]
  • Handley Page Pacific[21]
  • Hawker P.1121: BOl.21R[21]
  • Hawker P.1129 to OR339: BOl.15R[21]
  • Martin/General Dynamics RB-57F Canberra: Mk 701 developed from Mk 301.[21]
  • Gloster P492/3: Mk 591[21]
  • Republic F-105 Thunderchief: BOl.21 for possible sale to RAF.[21]
  • Saab 36[24]
  • Saab 37 Viggen[25]
  • Vickers VC10: Development of Mk 555 with aft fan.[21]

Engines on display

Specifications (Olympus 101)

Data from "The Operational Olympus". Flight. Archived from the original on 29 July 2013. and Lecture Notes, Vulcan Bristol Aero Engine School

General characteristics

  • Type: axial flow two-spool turbojet
  • Length: 127.1 in (10.59 ft; 3.23 m)
  • Diameter: 40 in (3.3 ft; 1.0 m)
  • Dry weight: 3,615 lb (1,640 kg)

Components

  • Compressor: axial 6 LP stages, 8 HP stages
  • Combustors: cannular 10 flame tubes
  • Turbine: HP single stage, LP single stage
  • Fuel type: AVTUR or AVTAG

Performance

See also

Related development

Comparable engines

Related lists

References

Notes
Citations
  1. ^ "The Rolls-Royce Olympus Aircraft Engine". Air Power World. Retrieved 2016.
  2. ^ "Rolls-Royce Olympus". Gatwick Aviation Museum. Retrieved 2016.
  3. ^ Baxter 2012, p. 16
  4. ^ http://www.flightglobal.com/pdfarchive/view/1955/1955%20-%201748.html
  5. ^ Baxter 2012, p. 20
  6. ^ Baxter 1990, pp. 10-13
  7. ^ Baxter 1990, pp. 13, 18
  8. ^ Baxter 1990, p. 13
  9. ^ http://webserver.dmt.upm.es/zope/DMT/Members/jmtizon/turbomaquinas/NASA-SP36_extracto.pdf p.44 and fig.27a
  10. ^ Baxter 1990, pp. 16, 18
  11. ^ a b Baxter 1990, p. 18
  12. ^ "Not Much of an Engineer" Sir Stanley Hooker, The Crowood Press Ltd. 2002, ISBN 9780906393352, p.142
  13. ^ "World Encyclopedia of Aero Engines - 5th edition" by Bill Gunston, Sutton Publishing, 2006, p36
  14. ^ Baxter 1990, p. 20
  15. ^ Baxter 1990, pp. 22, 24
  16. ^ Baxter 1990, p. 32
  17. ^ https://studylib.net/doc/8927942/supersonic-transport--sst--engines
  18. ^ Arrow Flight 25 October 1957, p. 647
  19. ^ a b c d "Archived copy". Archived from the original on 3 March 2016. Retrieved 2011.CS1 maint: archived copy as title (link) Avro Type List [1] Avro Heritage
  20. ^ Fildes 2012, p. 424
  21. ^ a b c d e f g h i j k l m n o p q r s t u v w x Baxter 1990, p. 172
  22. ^ Fildes 2012, p. 407
  23. ^ Addendum to Avro Brochure IPB 104
  24. ^ Wikipedia article quoting Berns, Lennart A36 - SAABs atombombare avslöjad, Flygrevyn issue No. 4, April 1991
  25. ^ [2] Historien om Viggen [3][permanent dead link]Protec 2005 No 4
Bibliography
  • Baxter, Alan. Olympus - the first forty years. Derby, UK: Rolls-Royce Heritage Trust, 1990. ISBN 978-0-9511710-9-7
  • Blackman, Tony. Vulcan Test Pilot. London, UK: Grub Street, 2009. ISBN 978-1-906502-30-0
  • Bullman, Craig. The Vulcan B.Mk2 from a Different Angle. Bishop-Auckland, UK: Pentland Books, 2001. ISBN 1-85821-899-3
  • Fildes, David W. The Avro Type 698 Vulcan Barnsley, UK: Pen % Sword Aviation, 2012, ISBN 978 1 84884 284 7
  • Hooker, Stanley. Not Much of an Engineer. Marlsborough, UK: Airlife Publishing, 2002. ISBN 978-1-85310-285-1

External links


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