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The result was a Bristol Mercury-sized engine adapted to the sleeve valve system, the Perseus, and its smaller cousin, the Bristol Aquila. The first production versions of the Perseus were rated at 580 horsepower (433 kW), the same as the Mercury model for that year, which shows that the sleeve system was being underexploited.
Pages in category "Bristol aircraft engines" The following 22 pages are in this category, out of 22 total. ... Bristol Pegasus; Bristol Perseus; Bristol Phoebus ...
The Aquila was a nine-cylinder single-row radial aircraft engine designed by the Bristol Engine Company starting in 1934. A sleeve valve engine, its basic design was developed from the Bristol Perseus. The Aquila was never used in production, but further developments led to the Bristol Hercules, Bristol Taurus, and Bristol Centaurus.
The Bristol Hercules is a 14-cylinder two-row radial aircraft engine designed by Sir Roy Fedden and produced by the Bristol Engine Company starting in 1939. It was the most numerous of their single sleeve valve (Burt-McCollum, or Argyll, type) designs, powering many aircraft in the mid-World War II timeframe.
Vehicle production was conducted at Patchway, Bristol. [1] The engine developed for the Bristol 400 found its way into many successful motor cars manufactured by other companies, such as Cooper, Frazer Nash and AC and, in 1954 and 1955, powered the Bristol 450 sports prototype to class victories in the 24 Hours of Le Mans race.
Fedden and Butler immediately turned to such a design, adapting the Mercury to become the Bristol Aquila, and the Pegasus as the Bristol Perseus. However, both of these engines quickly found themselves at the "low end" of the power spectrum as ever-larger aircraft designs demanded ever-larger engines to power them.
As built, the Botha I was powered by a pair of Bristol Perseus X radial engines, each driving a de Havilland Type 5/11 Hydromatic three-bladed constant-speed propeller. The engines, mounted on the central section of the wing in wide-chord cowlings, were fitted with controllable cooling grills. [4]
Powered by 890 hp (660 kW) Bristol Perseus XIIIC engines, it had a maximum weight takeoff in 750 ft (230 m) and the ability to maintain height or climb at 120 mph (190 km/h) on a single engine. Testing was successful, with the Flamingo being granted a certificate of airworthiness on 30 June 1939, [ 2 ] with an initial production run of twenty ...