Snecma M88

From Wikipedia, the free encyclopedia
  (Redirected from SNECMA M88)
Jump to: navigation, search
M88
M88-2 Engine.JPG
M88-2 Engine at Paris Air Show 2007
Type Turbofan
National origin France
Manufacturer Snecma
Major applications Dassault Rafale

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

Design and development[edit]

The original M88-1 was a demonstrator engine with a technology level similar to that of the 3 shaft RB199. The M88-2 is a much more advanced engine developed specifically for the Rafale. Unlike the EJ200 designed for the Eurofighter, the M88 has variable camber fan inlet guide vanes, an HP compressor with a sixth stage and an exhaust nozzle of the ejector type. The M88 delivers 50 kN (11,250 lbf) of dry thrust and 75 kN (17,000 lbf) in 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.

Variants[edit]

An additional improvement, the M88-2E4, reduces fuel consumption by up to 8% compared to the original M88-2.

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]

The program M88-X (9 tons) 91kN is a project led by Snecma in connection with the sale of Rafale to the United Arab Emirates . This variant ready in 2013 will develop 20.250 lbf (from 17,000 lbf (76 kN) currently) justified by the fact that they will operate in a hot weather countries and will be for interception operations. This program could be accelerated by the interest of potential customers such as Kuwait for a Rafale equipped with this engine. It could also equip the French air force in Tranche 4 Rafales ordered the engine to present the same costs of maintenance in operational conditions than previous versions (including "Pack CGP" and "-E4). The main change in this version is a low pressure compressor larger to increase the flow of engine 65 kg / s to 72 kg / s, with an overall pressure ratio of 27. The three floors of this module will be vaned disc monobloc.

Applications[edit]

Specifications (M88-2)[edit]

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
  • Air mass flow: 65 kg/s (143 lb/s)
  • 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[edit]

Comparable engines
Related lists

References[edit]

  1. ^ "Rafale Fighter Flies with Upgraded M88-4E Engine." Defense Talk, 7 May 2010.
  2. ^ 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[edit]