Armstrong Siddeley ASX
|The Armstrong Siddeley ASX|
|National origin||United Kingdom|
|First run||April 1943|
|Major applications||Avro Lancaster (test bed only)|
|Developed into||Armstrong Siddeley Python|
The ASX was an early axial flow jet engine built by Armstrong Siddeley that first ran in April 1943. Very little information on the engine is available, and it appears it was never put into production. A turboprop version as the ASP was somewhat more successful, and as the Armstrong Siddeley Python saw use in the Westland Wyvern.
Design and development
The ASX was unique in layout. The inlet to the 14-stage compressor was placed near the middle of the engine, the air flowing forward as it was compressed. From there it fed into 11 flame cans arranged around the outside of the compressor, flowing back past the inlet, and finally through the turbine.
This layout allowed the compressor and combustion areas to be "folded" together to make the engine shorter, although the overall reduction in the case of the ASX appears to be fairly limited. Additionally this makes it more difficult to service the compressor, although in modern designs it is the "hot section" that generally requires most servicing.
At full power the engine ran at 8,000 rpm and developed 2,600 lbf (12 kN) of thrust at sea level. For cruise the engine ran at 7,500 rpm and developed 2,050 lbf (9.1 kN). It weighed 1,900 lb (865 kg). The ASP conversion used a second turbine stage to drive the propeller through a gearbox, producing 3,600 shp, as well as 1,100 lbf (4.9 kN) of leftover jet thrust.
Beyond this, little has been published about this engine. Armstrong Siddeley appears to have given up on the design just after the war, and took over the Metrovick F.9 Sapphire design instead.
- Avro Lancaster (Test only)
- Type: Axial flow turbojet
- Length: 167 in (4,241.8 mm)
- Diameter: 42 in (1,066.8 mm)
- Dry weight: 1,900 lb (861.8 kg)
- Compressor: 14-stage axial reverse-flow compressor
- Combustors: 11 stainless steel can combustion chambers arranged around the compressor
- Turbine: 2-stage axial
- Fuel type: Kerosene (R.D.E. / F / KER)
- Oil system: pressure feed to bearings, dry sump, 80 S.U. secs (10.2 cs) (D.E.D. 2472D) grade oil
- Maximum thrust: 2,600 lbf (11.57 kN) at 8,000 rpm at sea level
- Overall pressure ratio: 5:1
- Turbine inlet temperature: 1,220 °F (660 °C)
- Specific fuel consumption: 1.03lb/lbf/hr (104.98 kg/kN/hr)
- Thrust-to-weight ratio: 1.37 lbf/lb (0.0134 kN/kg)
- Military thrust, static: 2,600 lbf (11.57 kN) at 8,000 rpm at sea level
- Cruising, static: 2,050 lbf (9.12 kN) at 7,500 rpm at sea level
- Idling, static: 130 lbf (0.58 kN) at 3,000 rpm at sea level
- Related development
- Related lists
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
- Jane's Fighting Aircraft of World War II. London. Studio Editions Ltd, 1998. ISBN 0-517-67964-7
- Smith, Geoffrey G.Gas Turbines and Jet Propulsion for Aircraft, London S.E.1, Flight Publishing Co.Ltd., 1946.
- Kay, Anthony L. (2007). Turbojet History and Development 1930-1960. 1 (1st ed.). Ramsbury: The Crowood Press. ISBN 978-1-86126-912-6.
- Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 282–283.
- Bridgman, Leonard, ed. (1947). Jane's all the World's Aircraft 1947. London: Sampson Low, Marston & Co. pp. 3d–4d.