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The engine is a V-twin four-stroke, 895 cc (54.6 cu in) or 993 cc (60.6 cu in) displacement, fan-driven air-cooled, gasoline engine design.The larger displacement is achieved by increasing the stroke from 78 to 87 mm (3.1 to 3.4 in), but using the same bore of 86 mm (3.4 in).
The Patchway factory in South Gloucestershire produced military aeroplane engines including the Olympus two-spool turbojet (from which the engine for Concorde was developed), the Orpheus turbojet for the Folland Gnat light fighter/trainer aircraft, the Pegasus two shaft medium bypass ratio vectored thrust turbofan for the Hawker Siddeley P.1127 ...
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 weight savings from deleting a bearing and associated parts listed below gave an engine with a thrust of 5,000 lbf but weighing only 800 lb. [2] [i] Eliminating the usual centre support bearing for the shaft joining the compressor and turbine meant the shaft would whirl, assuming a bowed shape, and damage the engine. Whirling was prevented ...
Examples of the BOl.1/2A were delivered to Curtiss-Wright in 1950. The engine was Americanised during 1951 and flew under a Boeing B-29 testbed as the TJ-32. Curtiss-Wright J67 To meet a USAF demand for an engine in the 15,000 lbf (67 kN) thrust class, the engine was the subject of a development contract, redesigned and designated J67.
Based on the 300-series Olympus, [1] the BS.100 was similar in general arrangement to that of the company's Pegasus design, but with the addition of plenum chamber burning (PCB), to enable the projected Hawker Siddeley P.1154 VSTOL fighter design to accelerate to supersonic speed [2] and to allow the aircraft to hover.
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