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Data from Rolls-Royce Heritage Trust General characteristics Type: Gas generator Length: Diameter: Dry weight: Components Compressor: 5-stage LP, 7-stage HP Combustors: 8 chamber, cannular Turbine: Single-stage LP and HP Performance Maximum power output: 28,500 shp (21.4 MW) Specific fuel consumption: 0.47 lb/hp/hr (0.287 kg/KWh) See also Related development Rolls-Royce Olympus References ^ a ...
The Rolls-Royce Olympus (originally the Bristol B.E.10 Olympus) was the world's second two-spool axial-flow turbojet aircraft engine design, first run in May 1950 and preceded only by the Pratt & Whitney J57, first-run in January 1950.
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.
The Rolls-Royce/Snecma Olympus 593 was an Anglo-French turbojet with reheat, which powered the supersonic airliner Concorde.It was initially a joint project between Bristol Siddeley Engines Limited (BSEL) and Snecma, derived from the Bristol Siddeley Olympus 22R engine.
The Rolls-Royce Marine Spey is a marine gas turbine based on the Rolls-Royce Spey and TF41 aircraft turbofan engines. [1] The Marine Spey currently powers seven ship classes including the Royal Navy's Type 23 frigates and provides a power output of 19.5 MW (about 26,150HP). The Marine Spey incorporates technology from the Tay and RB211.
The marine version, the Rolls-Royce Tyne RM1A, RM1C and RM3C remained in service as the cruise gas turbines in Royal Navy Type 21 frigates, Type 42 destroyers and Type 22 frigates until the retirement of the 4 Batch 3 Type 22 frigates (2011) and the last remaining Type 42 Destroyer (2013).
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