Bristol Orion
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| Bristol Orion on display at the Rolls-Royce Heritage Trust, Derby |
The Bristol Orion aero engine is a two-shaft turboprop intended for use in later marks of the Bristol Britannia and the Canadair CL-44. Although the engine was built and underwent a development program, the BE.25 Orion project was cancelled in 1958 by the British Ministry of Supply in favour of the Rolls-Royce Tyne.[1] In addition, interest in turboprop-powered aircraft was beginning to wane, because of the successful introduction of the Boeing 707 and Douglas DC-8 jetliners into airline service.[2]
The Orion gas generator had been chosen by French aircraft designer Wibault to power a vectored thrust aircraft[3] which ultimately became the Hawker Siddeley P.1127 but with a Bristol Siddeley Orpheus gas generator which had a compressor derived from the Orion low pressure compressor.[1]
Design and development
A single-stage HP turbine drove a five-stage all-axial HP compressor, while a three-stage LP turbine drove both the seven-stage LP compressor and the propeller, via a reduction gearbox. Thus the Orion used a shared-load LP turbine (like the Rolls-Royce Tyne), whereas its predecessor, the Bristol Proteus, had a free-power turbine. The combustor used separate flame cans.
One novel feature of the Orion was a derate from a thermodynamic rating of 9,000 shp at sea level, to enable a constant 5,150 ehp power level to be maintained up to 15,000 ft altitude.
The Orion project was cancelled in January 1958, at a reported total cost of £4.75 million (Expression error: Unrecognized punctuation character "[".).[4]
Applications
Specifications (BOn.1 Orion)
Data from Flightglobal archive.[5]
General characteristics
- Type: Twin-spool turboprop
- Length: Template:Cvt
- Diameter: Template:Cvt
- Dry weight: Template:Cvt
Components
- Compressor: 7-stage LP axial flow compressor ; 5-stage HP axial flow compressor
- Combustors: Cannular combustor with 10 flame tubes
- Turbine: Single-stage HP turbine, 3-stage LP turbine
- Fuel type: Kerosene / JP-1
- Oil system: 3 independent systems at Template:Cvt
Performance
- Maximum power output: Take-off Template:Cvt (equivalent horsepower)
- Overall pressure ratio: 10:1
- Air mass flow: Template:Cvt
- Specific fuel consumption: Template:Cvt (equivalent horsepower)
- Thrust-to-weight ratio: Template:Cvt (equivalent horsepower)
See also
Related development
Comparable engines
Related lists
References
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- ↑ a b Turbojet History And Development 1930-1960 - Volume 1 Great Britain and Germany, Antony L. Kay 2007, The Crowood Press Ltd., Template:ISBN, p.149
- ↑ Gunston 1989, p.35.
- ↑ Pegasus The Heart of the Harrier, Andrew Dow, Pen & Sword Aviation 2009, Template:ISBN, p.71/73
- ↑ Script error: No such module "Citation/CS1".
- ↑ Flightglobal archive, 1956. Retrieved: 31 December 2008
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Further reading
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