page_title: Rolls-Royce Olympus
section_title: Variants
hierarchical_section_title: Rolls-Royce Olympus / Variants
caption_attribution_description: English: Avro Vulcan XJ784 at CAF base Bagotville in 1978.
context_page_description: The Rolls-Royce Olympus was the world's first two-spool axial-flow turbojet aircraft engine design, dating from November 1946, although not the first to run or enter service. It was originally developed and produced by Bristol Aero Engines. First running in 1950, 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 and the TJ-38 'Zephyr'. The Olympus was also developed with success as marine and industrial gas turbines.
  Bristol Aero Engines merged with Armstrong Siddeley Motors in 1959 to form Bristol Siddeley Engines Limited, 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.
context_section_description: BOl.1/2A
  BOl.1/2B
  BOl.1/2C
  BOl.2
  BOl.3
  Of all the early initial developments, BOl.2 to BOl.5 (the BOl.5 was never built), perhaps the most significant was the BOl.3. Even before the Vulcan first flew, the Olympus 3 was being suggested as the definitive powerplant for the aircraft. In the event, the 'original' Olympus was continuously developed for the Vulcan B1. The BOl.3 was described in 1957 as "a high-ended product intermediate between the Olympus 100 and 200 series."
  BOl.4
  BOl.5
  not built
  BOl.6
  (Mk.200)
  BOl.7
  (Mk.201)
  BOl.7SR
  BOl.11
  (Mk.102)
  BOl.12
  (Mk.104)
  BOl.21
  (Mk.301)
  BOl.21R
  not built, proposed for R.A.E. Missile (A) designed to meet O.R. 1149 issued May 1956.
  BOl.22R
  (Mk.320)
  BOl.23
  not built, proposed with a 301 compressor, 22R turbine and reheat to give 25,000 lbf (110 kN) at take-off (reheat).
  Olympus Mk 100
  (BOl.1/2B) Similar to Olympus Mk 99 rated at 9,250 lbf (41.1 kN) thrust for second Vulcan prototype VX777. First flew September 1953.
  Olympus Mk 101
  (BOl.1/2C) Larger turbine, 11,000 lbf (49 kN) thrust for initial production Vulcan B1 aircraft. First flew (XA889) February 1955.
  Olympus Mk 102
  (BOl.11) Additional zero stage on LP compressor, 12,000 lbf (53 kN) thrust for later production Vulcan B1 aircraft.
  Olympus Mk 104
  (BOl.12) Designation for Olympus Mk 102 modified on overhaul with new turbine and burners, 13,000 lbf (58 kN) thrust initially, 13,500 lbf (60 kN) thrust on uprating, standard on Vulcan B1A.
  'Olympus 106'
  Used to describe the development engine for the Olympus 200 (BOl.6). Possibly a corruption of BOl.6 (Olympus 6).
  Olympus Mk 97
  This early engine tested an early annular combustion chamber. It was test flown on Bristol's Avro Ashton test bed WB493.
  Olympus Mk 201
  (BOl.7) Uprated Olympus Mk 200. 17,000 lbf (76 kN) thrust. Initial Vulcan B2 aircraft.
  Olympus Mk 202
  Disputed. Either Olympus Mk 201 modified with rapid air starter, or Olympus Mk 201 with redesigned oil separator breathing system. This was the definitive '200 series' engine fitted to Vulcans not fitted with the Mk 301. The restored Vulcan XH558 is fitted with Olympus Mk 202 engines.
  'Olympus Mk 203'
  Very occasional reference to this elusive mark of engine can be found in some official Air Publications relating to the Vulcan B2. It is also noted in a manufacturer's archived document dated circa 1960.
  Olympus Mk 301
  (BOl.21) Additional zero stage on LP compressor. 21,000 lbf (93 kN) thrust. Later Vulcan B2 aircraft plus nine earlier aircraft retrofitted. Later derated to 18,000 lbf (80 kN) thrust. Restored to original rating for Operation Black Buck.
  Olympus 510 series
  With a thrust in the region of 15,000 to 19,000 lbf (67 to 85 kN), the 510 series were civilianised versions of the BOl.6. A team was sent to Boeing at Seattle to promote the engine in 1956 but without success.
  Olympus 551
  The Olympus 551 'Zephyr' was a derated and lightened version of the BOl.6 and rated at 13,500 lbf (60 kN) thrust. The engine was the subject of a licence agreement between Bristol Aero Engines and the Curtiss-Wright Corporation – the engine being marketed in the US as the Curtiss-Wright TJ-38 Zephyr. There were hopes to fit the Olympus 551 to the Avro Type 740 and Bristol Type 200 trijet airliners which did not progress beyond the project stage. Curtiss-Wright also failed to market the engine.
  Mk.320
  The performance specification for the BAC TSR-2 was issued in 1962. It was to be powered by two BSEL Olympus Mk 320 (BOl.22R) engines each rated at 19,610 lbf (87.2 kN) dry and 30,610 lbf (136.2 kN) with reheat at take-off. The engine, which was re-stressed for supersonic flight at sea level, and over Mach 2.0 at altitude, and featured much use of high-temperature alloys such as titanium and Nimonic, was a cutting edge derivative of the Olympus Mk 301 with a Solar-type afterburner. The engine first ran in March 1961, soon achieving 33,000 lbf (150 kN), and was test flown in February 1962 in an underslung nacelle in the belly of Vulcan B1 XA894 and was demonstrated at the Farnborough Air Show in September. In December 1962 during a full power ground
caption: Avro Vulcan XJ784 at CFB Bagotville in 1978. It is powered by four Olympus Mk 301 engines, identified by their shorter and wider jet pipe nozzles.[55]
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