Turbomeca Aspin
| Aspin | |
|---|---|
| Type | Turbofan |
| National origin | France |
| Manufacturer | Turbomeca |
| First run | Template:Avyear |
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]
Variants
- Aspin I
- 200 kg (440 lb) thrust
- Aspin II
- 350 kg (770 lb) thrust
Applications
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)
Components
- 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)
Performance
- Maximum thrust:
- 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)
- Specific fuel consumption: 53 kg/kN/h (0.52 lb/lbf/h)
- Thrust-to-weight ratio: 2.632
See also
Related development
Comparable engines
Related lists
References
- Notes
- Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
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