Bristol Theseus
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Theseus was the Bristol Aeroplane Company's first attempt at a gas-turbine engine design, a turboprop that delivered just over 2,000 hp (1,500 kW). A novel feature was the use of a heat exchanger to transfer waste heat from the exhaust to the compressor exit. The engine was soon superseded by the Proteus design with more power, and the only use of the engine was in two Handley Page Hermes conversions.
[edit] Specifications (Theseus)
General characteristics
- Type: Turboprop
- Length: 81.85 in (2070 mm)
- Diameter: 54 in (1372 mm)
- Dry weight: 2205 lb (1000 kg)
Components
- Compressor: 8-stage axial, followed by a single centrifugal stage
- Combustors: 8 combustion chambers
- Turbine: Three-stage
- Fuel type: Aviation kerosene
Performance
- Power output: 2,220 hp (1,660 kW) + 825 lb (3.67 kN) residual thrust
- Fuel consumption: 272 Imp. gal (1237 l) /hour
- Power-to-weight ratio: 1.0 hp/lb
[edit] Reference
Bridgman, Leonard, ed. Jane’s All The World’s Aircraft 1951-1952. London: Samson Low, Marston & Company, Ltd 1951.
Bristol / Bristol Siddeley aero-engines
