Design and development
The development of the engine started at Ivchenko-Progress of Zaporizhzhia, Ukraine in 1999. The engine was originally intended for the Yakovlev Yak-130 trainer aircraft. An afterburning version, the AI-222-25F (from Russian/Ukrainian term "Форсаж") is also available with thrust vectoring.
In 2015, Russian manufacturer "Saljut" began to produce AI-222-25 without any Ukrainian involvement.
Variants
- AI-222-25
- AI-222-25F
- AI-222-25KVT
- AI-222-25KFK
- AI-222-28
- AI-222-28F
Specifications (AI-222-25)
Data from
General characteristics
- Type: Two-spool low-bypass turbofan
- Length: 1,960 mm (77.17 in)
- Diameter: 640 mm (25.20 in)
- Dry weight: 440 kg (970.03 lb) in base configuration, 560 kg (1,234.59 lb) in afterburning configuration
Components
- Compressor: axial, 2-stage LP compressor and 8-stage HP compressor
- Combustors: annular
- Turbine: 1-stage HP, 1-stage LP
Performance
- Maximum thrust: 2520 kgf / 24.7 kN (5,552.78 lbf) in takeoff mode (non-afterburning), 4200 kgf / 41.2 kN (9,262.13 lbf) afterburning.
- Overall pressure ratio: 15.43:1
- Bypass ratio: 1.19:1
- Turbine inlet temperature: 1,470 K (1,200 °C)
- Specific fuel consumption: 0.66 kg/(kgf h)
- Thrust-to-weight ratio: 5.68 (non-afterburning), 7.5 (afterburning)
