The Rolls-Royce Olympus Aircraft Engine
The Rolls-Royce Olympus axial-flow turbojet was designed by Bristol Aero Engines and first run in 1950, it was the world's first first two-spool axial-flow turbojet aircraft engine and was initially designated the Bristol B.E.10 Olympus. In 1959 Bristol Aero Engines merged with Armstrong Siddeley Motors becoming Bristol Siddeley Engines Limited which was taken over by Rolls-Royce in 1966, however the people developing the Olympus turbojet remained the same.
The Rolls-Royce Olympus was initially just used in the Avro Vulcan bomber, it was then further developed for supersonic flight in to the Bristol Siddeley Olympus B.Ol.22R for the doomed BAC TSR-2 programme in the early 1960's. When an engine was needed for the Concorde supersonic airliner the TSR-2's Siddeley Olympus B.Ol.22R was the obvious choice for development, the new version of the Olympus was the Rolls-Royce/SNECMA Olympus 593 Mk 610, SNECMA were responsible for the engines afterburner which gave the new Olympus 38,050 lbf (169 kN) of thrust with reheat and was the first turbojet to continuously use reheat in normal flight. It is of note that when the Concorde was withdrawn from service in November 2003 there were no Olympus engines flying anywhere in the the world, this changed on the 18th of October 2007 when restored Vulcan B2 XH558 once again took to the sky allowing the unique "Vulcan howl" from it's four Olympus engines to be heard once again in British skys.
|Rolls-Royce Olympus 101 Specifications: |
- Type: Axial flow two-spool turbojet
- Length: 152.2 in (387 cm)
- Diameter: 40 in (100 cm)
- Dry weight: 3,615 lb (1,640 kg)
- Compressor: Axial 6 LP pressure stages, 8 HP stages
- Combustors: Cannular 10 flame tubes
- Turbine: HP single stage, LP single stage
- Fuel type: AVTUR or AVTAG
- Maximum thrust: 11,000 lbf (49 kN)
- Specific fuel consumption: .817
- Power-to-weight ratio: 3.04:1
Rolls Royce Snecma Olympus
593 Mk 602 Concorde
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Rolls-Royce Olympus Aircraft Engine picture and Specifications