| Gabizo | |
|---|---|
 | |
| Turbomeca Gabizo on display | |
| Type | Turbojet |
| National origin | France |
| Manufacturer | Turbomeca |
| First run | 1954 |
The Turbomeca Gabizo was a small turbojet engine produced by Turbomeca from the 1950s. The components were designed to take the stresses of high-speed fighter aircraft with some variants featuring afterburner.
Applications
Specifications (Gabizo)
Data from Flight,[1] Aircraft engines of the World 1957[2]
General characteristics
- Type: Turbojet
- Length: 2,083 mm (82.01 in)
- Diameter: 670 mm (26.38 in)
- Dry weight: 265 kg (584 lb)
Components
- Compressor: Single stage axial plus single-stage centrifugal
- Combustors: Single annular combustion chamber
- Turbine: Single-stage axial
- Fuel type: Aviation kerosene / JP-1
- Oil system: Pressure spray with scavenge at 3.0 bar (43 psi)
Performance
- Maximum thrust:
- Take-off: 10.79 kN (2,426 lbf) at 18,000 rpm
- Maximum continuous: 8.6 kN (1,940 lbf)
- Overall pressure ratio: 5.2:1
- Air mass flow: 22 kg/s (49 lb/s) at 18,000 rpm
- Turbine inlet temperature:
- TIT: 1,113.15 K (1,544.00 °F; 840.00 °C)
- JPT: 923.15 K (1,202.00 °F; 650.00 °C)
- Specific fuel consumption: 1.00 lb/lbf/h (0.028 kg/N/ks)
- Thrust-to-weight ratio: 4.15
See also
Comparable engines
Related lists
References
- ↑ "Aero Engines 1956" (pdf). Flight and Aircraft Engineer. 69 (2468): 567–597. 11 May 1956. Retrieved 19 March 2019.
- ↑ Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (15th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 202–203.
Further reading
Wikimedia Commons has media related to Turbomeca Gabizo.
- Gunston, Bill (1989). World Encyclopaedia of Aero Engines (2nd ed.). Cambridge, England: Patrick Stephens Limited. ISBN 978-1-85260-163-8.
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