Snecma M88

The Snecma M88 is an afterburning turbofan engine developed by Snecma for the Dassault Rafale fighter.

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 afterburner.

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. the M88-2 consists of twenty-one modules for interchangeable and replaceable repairs without the need for recalibration or balancing.

An additional improvement, the M88-2E4, 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.

pecifications

jetspecs

type=twin-shaft, bypass turbofan engine
length=3531 mm (139 in)
diameter=698.5 mm (27.5 in) inlet
weight=897 kg (1,978 lb)
compressor=6-stage

Bypass ratio: 0.30:1
combustion=
turbine=2 single-staged turbines
fueltype=
oilsystem=
power=
thrust=
*11,250 lbf (50.04 kN) military thrust
*17,000 lbf (75.62 kN) with afterburner
compression=24.5:1
aircon=
turbinetemp=1,850°K (2,871°F)
fuelcon= dry 0.80 kg/(daN·h)
power/weight=
thrust/weight= approx. 8.5:1

External links

* [http://www.snecma.com manufacturer website]
* [http://www.snecma.com/IMG/pdf/M88-2_Anglais.pdf manufacturer specification sheet (pdf)]
* [http://www.flightglobal.com/articles/1999/06/09/51979/snecma-m88.html Flight Global article on M88-2]
* [http://www.snecma.com/rubrique.php3?id_rubrique=40&lang=en Snecma's description on M88]