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.

Gabizo
Turbomeca Gabizo on display
Type	Turbojet
National origin	France
Manufacturer	Turbomeca
First run	1954

Applications

• Breguet 1100
• Dassault Étendard II
• Fouga CM.171 Makalu
• SNCASO Trident

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

• Armstrong Siddeley Viper

Related lists

• List of aircraft engines

References

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.

На других языках

[fr] Turbomeca Gabizo