avia.wikisort.org - EngineThe Bristol Orion aero engine was 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]
1950s British turboprop aircraft engine
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 (equivalent to $118,061,042 in 2021).[4]
Applications
Specifications (BOn.1 Orion)
Data from Flightglobal archive.[5]
General characteristics
- Type: Twin-spool turboprop
- Length: 112.3 in (2,850 mm)
- Diameter: 41.8 in (1,060 mm)
- Dry weight: 3,240 lb (1,470 kg)
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 80 psi (550 kPa)
- Maximum power output: Take-off 5,150 shp (3,840 kW) (equivalent horsepower)
- Overall pressure ratio: 10:1
- Air mass flow: 82 lb/s (37 kg/s)
- Specific fuel consumption: 0.39 lb/hp/h (0.066 kg/kW/ks) (equivalent horsepower)
- Thrust-to-weight ratio: 1.63 hp/lb (2.68 kW/kg) (equivalent horsepower)
See also
Related development
Comparable engines
Related lists
References
- Turbojet History And Development 1930-1960 - Volume 1 Great Britain and Germany, Antony L. Kay 2007, The Crowood Press Ltd., ISBN 978 1 86126 912 6, p.149
- Gunston 1989, p.35.
- Pegasus The Heart of the Harrier, Andrew Dow, Pen & Sword Aviation 2009, ISBN 978 1 84884 042 3, p.71/73
- "Cancelled projects: the list up-dated". Flight: 262. 17 August 1967.
- Flightglobal archive, 1956. Retrieved: 31 December 2008
Further reading
На других языках
- [en] Bristol Orion
[fr] Bristol BE.25 Orion
Le Bristol BE.25 Orion était un turbopropulseur à double corps britannique, conçu par Bristol Aero Engines et prévu pour être utilisé sur les dernières versions du Bristol Britannia et du Canadair CL-44. Même si le moteur fut produit et fit l'objet d'un programme de développement complet, le BE.25 Orion fut abandonné en 1958 par le Ministry of Supply britannique. À ce moment-là, l'intérêt envers les avions turbopropulsés commençait à baisser, essentiellement à cause de l'introduction des avions de ligne Boeing 707 et Douglas DC-8 en service civil[1].
Текст в блоке "Читать" взят с сайта "Википедия" и доступен по лицензии Creative Commons Attribution-ShareAlike; в отдельных случаях могут действовать дополнительные условия.
Другой контент может иметь иную лицензию. Перед использованием материалов сайта WikiSort.org внимательно изучите правила лицензирования конкретных элементов наполнения сайта.
2019-2025
WikiSort.org - проект по пересортировке и дополнению контента Википедии