Turbomeca Aspin
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Turbomeca Aspin
Type Turbofan
Manufacturer Turbomeca
First run 1951

The Turbomeca Aspin was a small French turbofan engine produced by Turbomeca in the early 1950s. This geared turbofan design was the first turbofan to fly, powering the Fouga Gemeaux test-bed aircraft on 2 January 1952.[1]


Aspin I
200 kg (440 lb) thrust
Aspin II
350 kg (770 lb) thrust


Specifications (Aspin II)

Data from Aircraft engines of the World 1953 [2]

General characteristics

  • Type: Geared turbofan
  • Length: 1,614 mm (63.5 in)
  • Diameter: 604 mm (23.8 in)
  • Dry weight: 138 kg (304 lb)


  • Compressor: single-stage geared axial flow fan, single-stage centrifugal flow compressor
  • Combustors: Annular combustion chamber
  • Turbine: Two-stage axial flow turbine
  • Fuel type: Kerosene
  • Oil system: Dry sump, Turbomeca gear pump at 5.9 bar (85 psi)


Take-off: 3.6 kN (800 lbf)
Max Continuous: 3.14 kN (705 lbf)
Fan: 1.15:1 at 35,000 rpm / sea level
Compressor: 3.8:1 at 35,000 rpm / sea level
  • Air mass flow:
Fan:21 kg/s (46 lb/s) at 35,000 rpm / sea level
Compressor:3.0 kg/s (6.6 lb/s) at 35,000 rpm / sea level
  • Turbine inlet temperature:
Before turbine:810 °C (1,490 °F; 1,080 K)
After turbine:560 °C (1,040 °F; 833 K)

See also

Related development

Comparable engines

Related lists


  1. ^ Gunston 1989, p. 169.
  2. ^ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 166-167.
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9

External links

  This article uses material from the Wikipedia page available here. It is released under the Creative Commons Attribution-Share-Alike License 3.0.



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