Development of the AI-222 engine was started by Ivchenko-Progress in Zaporozhye, Ukraine in 1999. Development was completed in 2008. It is based on the AI-22 engine. However, it has a modified combustion chamber and high and low pressure turbine design compared to the AI-22. The high-pressure turbine is unified with the turbine of the D-27 engine. At the customer's request, the engine can be fitted with thrust vectoring nozzles (20° in any direction from the engine axis) and a forcing chamber. The engine uses a digital automatic control system in combination with test and diagnostic systems (FADEC).
The engine is primarily designed to power Yak-130 aircraft. In the AI-222K-25F version (with afterburner), it powers the Hongdu L-15 Lift (Lead in fighter training) aircraft. 250 of these engines are to be produced by 2015.
AI-222-25
Twin-shaft, two-stage jet engine with 8-stage axial compressor and annular combustion chamber, high and low pressure turbines
Manufacturer:
Motor Sic
FGUP Salut
Length: 1960 mm (77.17 in)
Diameter: 640 mm (25.20 in)
Dry weight: 440 kg (970.03 lb)
Compressor: axial
Maximum thrust: 24.7 kN (2,518.70 kgf) (for takeoff mode)
Engine thrust for maximum power at 5 km altitude at M = 0,6 - 14,5 kN
Engine thrust in cruise mode at 10 km altitude and M = 0.6 is 3 kN kg
Overall pressure ratio: 15.43:1
Bypass ratio: 1.19:1
Turbine inlet temperature: 1,470 K (1,197 °C)
Specific fuel consumption: 0.64 kg/kgf-hr
AI-222-25F
Thrust with afterburner at sea level - 42 kN
Thrust at 11 km altitude at Mach 1.4 27.60 kN
Engine weight 560 kg
Source:
http://ru.wikipedia.org/wiki/%D0%90%D0%98-222-25
The engine is primarily designed to power Yak-130 aircraft. In the AI-222K-25F version (with afterburner), it powers the Hongdu L-15 Lift (Lead in fighter training) aircraft. 250 of these engines are to be produced by 2015.
AI-222-25
Twin-shaft, two-stage jet engine with 8-stage axial compressor and annular combustion chamber, high and low pressure turbines
Manufacturer:
Motor Sic
FGUP Salut
Length: 1960 mm (77.17 in)
Diameter: 640 mm (25.20 in)
Dry weight: 440 kg (970.03 lb)
Compressor: axial
Maximum thrust: 24.7 kN (2,518.70 kgf) (for takeoff mode)
Engine thrust for maximum power at 5 km altitude at M = 0,6 - 14,5 kN
Engine thrust in cruise mode at 10 km altitude and M = 0.6 is 3 kN kg
Overall pressure ratio: 15.43:1
Bypass ratio: 1.19:1
Turbine inlet temperature: 1,470 K (1,197 °C)
Specific fuel consumption: 0.64 kg/kgf-hr
AI-222-25F
Thrust with afterburner at sea level - 42 kN
Thrust at 11 km altitude at Mach 1.4 27.60 kN
Engine weight 560 kg
Source:
http://ru.wikipedia.org/wiki/%D0%90%D0%98-222-25