Saturn AL-31

Saturn AL-31

is a military turbofan engine. Saturn AL-31 originally made for the Sukhoi Su-27 air superiority fighter. Saturn AL-31 was developed by Lyulka, now NPO Saturn, of Russia (former Soviet Union).

Type : Turbofan
National origin : Russia
Manufacturer : NPO Saturn
Major applications : Sukhoi Su-27, Chengdu J-10

Saturn AL-31 produces a total thrust of 123 kN (27,600 lb) with afterburning in the AL-31F, 137 kN (30,800 lb) in the AL-31FM (AL-35F) and 142 kN (32,000 lb) in the AL-37FU variants.
Variants

Name Description Builder Year Thrust Thrust vectoring Aircraft Status
Al-31F The basic engine developed to power the Su-27 fighter Salyut, UMPO 1981 123 kN (27,700 lbf) No Su-27, Shenyang J-11, Sukhoi Su-30MKK, Sukhoi Su-30(Salyut) In service/production
Al-31FP Improved variant for the Indian Su-30MKI with thrust vectoring Salyut, HAL 2000 123 kN (27,700 lbf) Yes Su-30 MKI, Sukhoi Su-30MKM In service/production
Al-31FN Improved variant for the Chengdu J-10 Salyut 2002 125 kN (28,100 lbf) No Chengdu J-10 In service/production
Al-31FM Improved version for the Russian Air Force Salyut 2007 132 kN (29,700 lbf) Yes Su-27SM, Su-30, Su-34 In service/production
Al-41F-1S (117S) Advanced derivative for the Su-35 UMPO 2010 142 kN (31,900 lbf) Yes Su-35 In service/early production
Al-41F-1 (117) Advanced derivative for the Sukhoi PAK FA UMPO 2010 147 kN (33,000 lbf) Yes PAK FA prototype In service/early production

Saturn AL-31 Specifications

General characteristics

  • Type: Two-shaft afterburning turbofan
  • Length: 4,990 millimetres (196 in)
  • Diameter: 905 millimetres (35.6 in) inlet; 1,280 millimetres (50 in) maximum external
  • Dry weight: 1,570 kilograms (3,500 lb)

Components

  • Compressor: 4 fan and 9 compressor stages
  • Combustors: annular
  • Turbine: 2 single-staged turbines

Performance

  • Maximum thrust:
    74.5 kilonewtons (16,700 lbf) military thrust
    122.58 kilonewtons (27,560 lbf) with afterburner
  • Bypass ratio: 0.59:1
  • Turbine inlet temperature: 1685 K (1,412 °C (2,574 °F))
  • Fuel consumption: 2.0 Kg/daN·h
  • Specific fuel consumption:
    Military thrust: 0.67 lb/(lbf·h)Full afterburner: 1.92 lb/(lbf·h)
  • Thrust-to-weight ratio: 7.14
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