Turbomeca Gabizo
| 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]
General characteristics
- Type: Turbojet
- Length: 218 cm (86 in)
- Diameter: 67.3 cm (26.5 in)
- Dry weight: 255 kg (560 lb)
Components
- Compressor: Single stage axial plus single-stage centrifugal
- Combustors: Single annular combustion chamber
- Turbine: Single-stage
Performance
- Maximum thrust: 10.78 kN (2,426 lbf)(maximum thrust) 8.62 kN (1,940 lbf)(maximum continuous thrust)
- Overall pressure ratio: 5.1:1
- Air mass flow: 14.7 kg/s (32.6 lb/s)
- Specific fuel consumption: 1.04
- Thrust-to-weight ratio: 0.042 kN/kg (4.332 lbf/lb)
See also
- Comparable engines
- Related lists
References
 |
Wikimedia Commons has media related to Turbomeca Gabizo. |
Notes
- ↑ Turbomeca Gabizo - Flight, 11 May 1956 www.flightglobal.com Retrieved: 7 April 2010
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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