Armstrong Siddeley ASX

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The Armstrong Siddeley ASX was a jet engine , of which the British manufacturer Armstrong Siddeley made a prototype in April 1943. There is little information about this engine, which probably never went into series production. The Armstrong Siddeley ASP turboprop version was much more successful and was built into the Westland Wyvern as a Python .

construction and development

The ASX was unique in its kind. The air inlet to the compressor was located in the middle of the machine so that the air had to flow forward during compression. From there it flowed through 11 flame tubes on the outside of the compressor, past the air inlet and finally through the turbine . So you could "fold" the compressor and the combustion chambers in order to make the whole machine shorter, even if the shortening in the case of the ASX was not particularly great. In addition, this created difficulties in maintaining the compressor, even if the “hot areas” require the most maintenance in modern designs.

The flight tests of the ASX took place in the bomb pit of an Avro Lancaster with registration no. ND784 instead. The first flight took place on September 28, 1945.

At full power, the machine ran at 8000 rpm. and developed 12 kN of thrust at a height of 0 m. In flight operations, the engine ran at 7500 rpm. and delivered a thrust of 9.1 kN. It weighed 865 kg. The ASP turboprop version had a second turbine stage to drive the propeller via a reduction gear and developed 3600 shp of power and 4.9 kN of residual thrust.

In addition, little has been published about this jet engine. Armstrong Siddeley appears to have abandoned the design after World War II and instead adopted the Metrovick F.9 - Sapphire design.

Aircraft with Armstrong Siddeley ASX

Data (ASM.3)

General

  • Type: jet engine
  • Length: 4241.8 mm
  • Diameter: 1066.8 mm
  • Weight: 861.8 kg

Components

  • Compressor: axial, 14-stage, reverse flow
  • Combustion chambers: 11
  • Turbine: axial, 2-stage
  • Fuel: kerosene
  • Lubrication: dry sump with pressure lubrication of the bearings, 10.2 cs oil (DED 2472D)

power

  • Maximum thrust: 11.57 kN at 8000 rpm. at a height of 0 m
  • Thrust in flight operation: 9.12 kN at 7500 rpm. at a height of 0 m
  • Idle thrust: 0.58 kN at 3000 rpm. at a height of 0 m
  • Total print ratio: 5: 1
  • Inflow temperature at the turbine: 660 ° C
  • Specific fuel consumption: 104.98 kg / kN xh
  • Push weight: 74.486 kg / kN

Individual evidence

  1. ^ Bill Gunston: World Encyclopedia of Aero Engines . Patrick Stephens, Cambridge 1989. ISBN 1-85260-163-9 . P. 18.
  2. ^ Geoffrey G. Smith: Gas Turbines and Jet Propulsion for Aircraft . Flight Publishing, London 1946. p. 89.
  3. ^ Paul H. Wilkinson: Aircraft Engines of the World 1946 . Sir Isaac Pitman & Sons, London 1946. pp. 282-283.

literature

  • Bill Gunston: World Encyclopedia of Aero Engines . Patrick Stephens, Cambridge 1989. ISBN 1-85260-163-9
  • Geoffrey G. Smith: Gas Turbines and Jet Propulsion for Aircraft . Flight Publishing, London 1946.
  • Paul H. Wilkinson: Aircraft Engines of the World 1946 . Sir Isaac Pitman & Sons, London 1946.
  • Anthony L. Kay: Turbojet History and Development 1930-1960 . 1st edition. The Crowood Press, Ramsbury 2007. ISBN 978-1-86126-912-6 .

Web links