Russia completely indigenize Ukrainian components on AI-225 turbofan engine

Russian jet engine manufacturer, Salut has successfully completed testing of the fully indigenised version of the Ivchenko Progress AI-225-25 low bypass turbofan engine, which powers the Yakovlev Yak-130 combat trainer aircraft.

The Ukrainian components, which earlier consisted half of the engine has been completely replaced by Russian made parts, following suspension of military and diplomatic relations between the two countries due to the Crimean crisis.

The localized engine demonstrated improved reliability and extended service life, during ground testing carried out on the first indigenous engine manufactured by Salyut.

Service life and mean time before overhaul (MTBO) of Salyut manufactured AI-225-25 engines have now more than doubled. The MTBO increased to 1,500 flight hours from the earlier 600 hours and service life increased to 3,000 hours from 1,200 hours.

Localisation of the engine was completed in 2015, and is currently being produced at Salyut's Moscow factory. Company has already supplied the engine to Russian armed forces and is also providing comprehensive after sale support services.

Since introduction into Russian service in 2012, more than 80 Yak-140 trainers have been delivered by Irkut Corporation.

The Yak-140 is powered by two AI-225-25 engines rated at 24.5 kN thrust each. The engine features a two-stage axial low-pressure compressor, an eight stage high-pressure compressor, an annular single-stage combustion chamber, a single-stage cooled turbine of high and uncooled low-pressure turbine.

The FADEC controlled engine with a bypass ratio of 1.18 has a compressor ratio of 15.4 and weights 440 kg when dry.

Source: aviationanalysis.net

AI-225-25

AI-225-25 is intended to power trainer and light combat planes such as Yak/AEM-130 or others like L-159 etc. Engine is characteristic in maximal safety and high efficiency. Modular construction, FADEC, diagnostic system and high lifetime are standard for all new modern engines. To lower the R&D cost, the engine's core is similar to the one in AI-22 for Tu-324 reginal jets. The AI-22 bench tests started on 25to September 2001. The production documentation od AI-222-25 was transfered to Sajult and Motor Sich on 2th October 2001. AI-222-25's core ground tests began in September 2002, first flight test was conducted in June 2003 and in December two engines were installed on Yak-130. First Yak-130 took off on 30th April 2004. In December 2004 another two engines were delivered for the second Yak-130. Goverment tests were planned for the first half of 2006.

AI-222-25's scheme

• 2-stage titanium fan
• 8-stage HPC with variable guide vanes and first and second stator blades
• annular combustion chamber with 16 fuel injectors and reduced emmision generation
• 1-stage HPT with air cooled guide vanes and turbine rotor
• 1-stage LPT with cooled guide vanes
• fixed convergent exhaust nozzle
• removable gearbox which can be relocated if the airplace construction demands it

AI-222-25

Type	-	AI-222-25
Thrust - maximal (H=0, M=0, t=30°C)	kp	2500
- maximal (H=5000 m, M=0,6)	kp	1450
- maximal (H=6000 m, M=0,4)	kp
- afterburner (H=0, M=0)	kp
- afterburner (H=11 km, M=1,4)	kp
- cruise (H=6000 m, M=0,5)	kp
- cruise (H=10000 m, M=0,6)	kp	300
SFC - maximal thrust (H=0, M=0, t=30°C)	kg.kp-1.h-1	0,64
- maximal thrust (H=5000 m, M=0,6)	kg.kp-1.h-1	0,87 3)
- afterburner (H=0, M=0)	kg.kp-1.h-1
- cruise (H=6000 m, M=0,5)	kg.kp-1.h-1
- cruise (H=10000 m, M=0,6)	kg.kp-1.h-1	0,875 3)
Airflow 1)	kg.s-1	50,2
Overall pressure ratio 1)	-	15,9
Bypass ratio	-	1,19
Maximal turbine inlet temperature	°C	1210
Inlet diameter	mm
Maximal diameter	mm
Length	mm	2237,7
Width	mm	860
Height	mm	1093
Dry weight	kg	440
Lifespan	h	3000

1) Airflow and overall pressure ratio is valid for H=0, M=0, t=30 °C.

2) 2800 kp valid for P=760 mm Hg, T=30°C, thrust in conditions P=746 mm Hg, T=27°C is 2830 kp.

3) Values are from the same source but a few years older and maybe obsolete

The engine can be equiped with omnidirectional thrust vector control on customers demand. The nozzle deflects gas by 20°. New engine is then designated AI-222-25UVT.

The other version, AI-222-28 has upgraded turbine cooling system which made the thrust augmentation possible. Cooling system was taken from turboprop engine D-27. The thrust is now 2800 kp.

AI-222-25F modification has an afterburner and thrust 4200 kp (68% gain). Engine is designed for future supersonic light compat planes with speed up to M=1.5.

Source: leteckemotory.cz

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