The Snecma M88 is a French afterburning turbofan engine developed by Snecma for the Dassault Rafale fighter.
Variants
The M88 Pack CGP (for "total cost of ownership") or M88-4E is based on a study contract, development and production reported in 2008 by the General Delegation for Armament and is to introduce technical improvements to reduce maintenance costs. The purpose of this release is to reduce cost of ownership of the M88 and longer inspection intervals of the main modules by increasing the lifetime of the hot and rotating parts. It has been tested in flight for the first time March 22, 2010 at Istres, the Rafale's M02 CEV.[1]
Applications
Specifications (M88)
Data from [2]
General characteristics
- Type: Twin-shaft, turbofan engine
- Length: 3538 mm (139.3 in)
- Diameter: 696 mm (27.5 in) max
- Dry weight: 897 kg (1,977 lb)
Components
- Compressor: 3 stage low pressure, 6 stage high pressure
- Combustors: Annular
- Turbine: single stage high pressure, single stage low pressure
Performance
- Maximum thrust: 50 kN (11,250 lbf) dry, 75 kN (16,900 lbf) wet (afterburning)
- Overall pressure ratio: 24.5:1
- Bypass ratio: 0.3
- Turbine inlet temperature: 1,850K (1,577 °C)
- Fuel consumption: 0.80 kg/(daN*h) (0.78 lbm/(lbf*h)) (dry), 1.75 kg/(daN*h) (1.72 lbm/(lbf*hr)) (wet/afterburning)
- Thrust-to-weight ratio: 5.7:1 (dry), 8.5:1 (wet/afterburning)
See also
- Comparable engines
- Related lists
References
- ↑ "Rafale Fighter Flies with Upgraded M88-4E Engine." Defense Talk, 7 May 2010.
- ↑ Desclaux, Jacques and Jacques Serre (2003). M88 – 2 E4: Advanced New Gengeration Engine for Rafale Multirole Fighter. AIAA/ICAS International Air and Space Symposium and Exposition: The Next 100 Years. 14–17 July 2003, Dayton, Ohio. AIAA 2003-2610.
External links
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