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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. [1] [2] It is best known as the powerplant of the Avro Vulcan and later models in the Concorde SST.
Olympus 593 on display at the Imperial War Museum Duxford. The Rolls-Royce/Snecma Olympus 593 was a reheated version of the Olympus which powered the supersonic airliner Concorde. [32] The Olympus 593 project was started in 1964, using the TSR2's Olympus Mk 320 as a basis for development. [33] BSEL and Snecma Moteurs of France were to share the ...
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.
In 1946 he was entrusted with the design of the Olympus engine, which performed flawlessly on its very first test bed run, largely as a result of the discipline that Gordon Lewis brought to its design. [See Pegasus The Heart of the Harrier, by Andrew Dow.] The Olympus was later developed to power the Avro Vulcan, TSR-2 and Concorde.
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 SNECMA M45, also called the SNECMA Mars, was a turbojet engine designed and produced by SNECMA in France during the late 1950s and early 1960s. The M45 was the precursor to a family of turbojet and turbofan engines, culminating in the collaborative Rolls-Royce/SNECMA M45H, high bypass turbofan engine.
The rating for an Olympus 593 would be somewhat higher. "Due to the high inlet air temperatures at Mach 2 cruise - in excess of 120 °C (393 K; 248 °F)" - actual temperature of the air entering the compressor was ~ 600 °C (873 K; 1,112 °F) — Preceding unsigned comment added by 86.8.126.91 ( talk ) 09:39, 23 January 2024 (UTC) [ reply ]
It is built around an 0.72 scale of the GE90-110B/115B core [1] and contains a Pratt & Whitney fan and low-pressure system design. The competing Rolls-Royce Trent 900 was named as the lead engine for the then-named A3XX in 1996 and was initially selected by almost all A380 customers. However, the GE/PW engine increased its share of the A380 ...