Ivchenko AI-25
| AI-25 | |
|---|---|
| |
| Ivchenko-Progress AI-25TL turbofan engine | |
| Type | Turbofan |
| National origin | Soviet Union |
| Manufacturer | Ivchenko-Progress |
| First run | 1966 |
| Major applications | Yakovlev Yak-40 Aero L-39 Albatros Hongdu JL-8 |
| Number built | 9,360+ |
| Developed into | DV-2 |
The Ivchenko AI-25 is a family of military and civilian twin-shaft medium bypass turbofan engines developed by Ivchenko OKB of the Soviet Union and was the first bypass engine ever used on short haul aircraft in the USSR. The engine is still produced by Ukrainian based aircraft engine manufacturing company, Motor Sich.
Development
The AI-25 was designed to power the Yakovlev Yak-40 tri-jet airliner, often called the first regional jet transport aircraft, and is the starting point for the Lotarev DV-2 turbofan engine.[1] The project was launched in 1965, with the AI-25s first test flight in 1966, and finally cleared for production in 1967. In 1972, the AI-25 was selected for the Polish PZL M-15 Belphegor, the world's only jet-powered biplane. Development of the AI-25 continued and the uprated AI-25TL was designed for use by the Czechoslovak Aero L-39 Albatros military trainer with the first flight occurring in 1968. The L-39, would go on to become one of the most popular, and widespread trainer aircraft in the world, with over 3,000 L-39s produced, and with 2,900 examples still in active service today. A smaller version of the AI-25TL, the AI-25TLK has equipped the People's Republic of Chinas Hongdu L-11 fighter-trainer. The AI-25TLK is also licensed built in the People's Republic of China as the WS-11. Another variant of the AI-25, is the AI-25TLSh in the 1990s, which underwent flight testing by the Ukrainian Ministry of Defense in 2002. Ivchenko-Progress is currently marketing the AI-25TLSh as an upgrade to existing L-39 and JL-8 operators that would extend the service life of the aircraft and improve performance. The latest AI-25 is the AI-25TL Series 2 designed for the Mikoyan MiG-AT.[2]
Applications
Specifications (AI-25TL)
Data from [3]
General characteristics
- Type: Turbofan
- Length: 3,350 mm (132 in)
- Diameter: 1,000 mm (39 in)
- Dry weight: 350 kg (770 lb)
Components
- Compressor: Axial, 3 fan/low pressure compressor stages, 9 high pressure compressor stages
- Combustors: Annular
- Turbine: 2 high pressure turbine stages, 1 low pressure turbine stages
Performance
- Maximum thrust: 16.9 kN (3,800 lbf)
- Overall pressure ratio: 9.5:1
- Specific fuel consumption: 130,5 kg/kN/h (1.28 lb/lbf·hr)
- Thrust-to-weight ratio: 4.9:1
See also
Related development
Comparable engines
Related lists
Notes and references
- ^ "AI-25". Retrieved 2009-02-21.
- ^ "More detailed information about AI-25 engine family". Retrieved 2009-02-20.
- ^ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 120.
External links
