SNECMA M88
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The M88 is an afterburning turbofan engine developed for the Dassault Rafale omnirole fighter by Snecma.
Although the M88 engine cycle is similar to that of the Eurojet EJ200, it is smaller and lower in thrust. Other differences are that the M88 has fan variable camber inlet guide vanes, the HP compressor has a 6th stage and the exhaust nozzle is of the ejector type. The M88 delivers 50 kN (11,250 lbf) of dry thrust and 75 kN (17,000 lbf) on full reheat.
Like its contemporaries, it features state of the art technologies such as single-crystal high-pressure turbine blades, powder metallurgy discs and full authority digital engine controls. The M88-2 was built with easy maintainability and reduced operating costs in mind. Twenty-one modules consist of the M88-2 for interchangeable and replaceable repairs without the need for recalibration or balancing.
An additional improvement, the M88-2E4 edition, reduces fuel consumption by up to 2 to 4% compared to the original M88-2.
An M88-3 variant is currently in development as of 2000. It will feature a new LP compressor and variable stator vane stage, reducing fuel consumption.
[edit] Specifications
General characteristics
- Type: twin-shaft, bypass turbofan engine
- Length: 3531 mm (139 in)
- Diameter: 698.5 mm (27.5 in) inlet
- Dry weight: 897 kg (1,978 lb)
Components
- Compressor: 6-stage
- Bypass ratio: 0.30:1
- Turbine: 2 single-staged turbines
Performance
- Thrust:
- 11,250 lbf (50.04 kN) military thrust
- 17,000 lbf (75.62 kN) with afterburner
- Overall pressure ratio: 24.5:1
- Turbine inlet temperature: 1,850°K (2,871°F)
- Fuel consumption: 0.80 kg/(daN·h)
- Thrust-to-weight ratio: approx. 8.5:1
[edit] External links
- manufacturer website
- manufacturer specification sheet (pdf)
- Flight Global article on M88-2
- Snecma's description on M88
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