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Lyulka AL-31
Saturn AL-31
UMPO 117

Saturn AL-31 FN


The Saturn AL-31 is a family of military twin spool turbofan turbofan engines. It was developed by Lyulka, later NPO Saturn, of the Soviet Union, originally for the Sukhoi Su-27 air superiority fighter. It 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. It powered all Su-27 derivatives and the Chengdu J-10 multirole jet fighter which was developed in China.

The AL-31FP and AL-37FU variants have thrust vectoring. The former is used in the Su-30MKI export version of the Su-30 for India & Sukhoi Su-30MKM for Malaysia . The AL-37FU can deflect its nozzle to a maximum of ±15° at a rate of 30°/sec. The vectoring nozzle is utilized primarily in the pitch plane. The Al-31FP is built in India by HAL at the Koraput facility under a deep technology transfer agreement.

It has a reputation for having a tremendous tolerance to severely disturbed air flow. In the twin-engined Su-27, the engines are interchangeable between left and right. The Mean Time Between Overhaul (MTBO) for the AL-31F is given at 1000 hours with a full-life span of 3000 hours. Some reports suggested that Russia was offering AL-31F to Iran to re-engine its F-14 Tomcat air fleet in the late 1990s.

According to Saturn`s Victor Mihailovic Chepkin, chief designer of the 117 and 117S engines, the Chinese WS-10 was developed with the aid of the AL-31`s maintenance technical documentation. China can domestically produce most AL-31 parts for its own jet engine programs, but must import turbine blades from Russia.

The 117S (AL-41F1A) is an upgrade of the AL-31F based on the AL-41F intended to power the Su-35BM, producing 142 kN (32,000 lb) of thrust in afterburner and 86.3 kN (19,400 lb) dry. It features a fan 3% larger in diameter (932 millimetres (36.7 in) versus 905 millimetres (35.6 in)), advanced high- and low-pressure turbines, an all-new digital control system, and provisions for thrust-vectoring nozzles similar to the AL-31FP. This engine will have an assigned life of 4,000 hours and an MTBO of 1,000 hours. The first flight of this engine was completed in an Su-35BM on 20 February 2008. On 9 August 2010, Ufa-based company UMPO started supplying 117S engines (AL-41F1S) intended for Su-35S fighters.

The 117 (AL-41F1) is a 5th generation engine custom built for Russia’s fifth-generation stealth fighter jet PAK-FA according to Sukhoi General Director Mikhail Pogosyan. Mikhail Pogosyan has clarified that claims that fifth-generation fighter allegedly has an old engine are wrong. Though most parameters of the new 5th Gen Engine are classified General Director Mikhail Pogosyan provided some information on the new engine, The engine thrust was enlarged by 2.5 tonnes when compared with the AL-31 engine, while the engine weight was cut by 150 kilograms. That allowed the new jet to supercruise i.e. move at a supersonic cruise speed without the use of after burner.
The Saturn Research and Production center made digitally controlled system (FADEC) of Project 117 Engine.The new engine produces 33,000 lbs (147 kN) of thrust in afterburner has a Dry weight of 1420 kilogram and T:W ratio of 10.5:1.
Mikhail Pogosyan further mentioned that this engine (117) meets the client’s (Russian AirForce) requirements. This is not an intermediate product made particularly for test flights. The engine was to be installed in production PAK-FA fighter which will be supplied to the Russian Air Force and prospective foreign clients.
Bench testing of a radically new engine (the second stage) for the Russian fifth generation fighter aircraft PAK FA will start in 2014, said the general designer-director of the Scientific and Technical Center "Saturn", Eugeny Marchuk "The engine will be ready in two years, and will begin bench testing then", said Marchuk at the 11th International Conference" Aviation and Space - 2012 ", which opened at the Moscow Aviation Institute. According to him, the new "engine 117" will belong to the "5 +" generation and its characteristics will be superior to the existing foreign counterparts engine for fifth generation aircraft. "This is - a fundamentally new engine, The motor unit weight is 30% less (than the 117C - approx.), Life-cycle costs will by 30% less, and it should be cheaper, "- said Marchuk.


Sukhoi Su-27
Sukhoi Su-30
Sukhoi Su-34
Sukhoi Su-36
Sukhoi S-37 Berkut

The basic engine developed to power the Su-27 fighter
Builder: Salyut, UMPO
Year: 1981
Thrust: 123 kN (27,700 lbf)
Thrust vectoring: No
Aircraft: Su-27, Shenyang J-11, Sukhoi Su-30MKK, Sukhoi Su-30(Salyut)


Improved variant for the Indian Su-30MKI with thrust vectoring
Builder: Salyut, HAL
Year: 2000
Thrust: 123 kN (27,700 lbf)
Thrust vectoring: Yes
Aircraft: Su-30 MKI, Sukhoi Su-30MKM


Improved variant for the Chengdu J-10
Builder: Salyut
Year: 2002
Thrust: 125 kN (28,100 lbf)
Thrust vectoring: No
Aircraft: Chengdu J-10


Improved version for the Russian Air Force
Builder: Salyut
Year: 2007
Thrust: 132 kN (29,700 lbf)
Thrust vectoring: Yes
Aircraft: Su-27SM, Su-30, Su-34


Improved version for the Russian Air Force
Builder: Salyut
Year: 2012
Thrust: 145 kN (32,600 lbf)
Thrust vectoring: Yes
Aircraft: Su-27SM, Su-30, Su-34


Al-41F-1S (117S)
Advanced derivative for the Su-35
Builder: UMPO
Year: 2010
Thrust: 142 kN (31,900 lbf)
Thrust vectoring: Yes
Aircraft: Su-35


Advanced derivative for the Su-37
Builder: UMPO
Thrust: 145 kN (32,600 lbf)
Thrust vectoring: Yes
Aircraft: Su-37


Al-41F-1 (117)
Advanced derivative for the Sukhoi PAK FA
Builder: UMPO
Year: 2010
Thrust: 147 kN (33,000 lbf)
Thrust vectoring: Yes
Aircraft: PAK FA prototype



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 (3,460 lb)
Compressor: 4 fan and 9 compressor stages
Combustors: annular
Turbine: 2 single-staged turbines
Maximum thrust:
74.5 kilonewtons (16,700 lbf) military thrust
122.58 kilonewtons (27,560 lbf) with afterburner
Overall pressure ratio: 23
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: 4.77:1 (dry), 7.87:1 (afterburning)





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