Lyulka AL-21
Turbojet aircraft engine
From Wikipedia, the free encyclopedia
The Lyulka AL-21 is an axial flow turbojet engine created by the Soviet Design Bureau named for its chief designer Arkhip Lyulka.
| AL-21 | |
|---|---|
| Lyulka AL-21F3 engine, Airforce Museum of the Bundeswehr; Berlin-Gatow | |
| Type | Turbojet |
| National origin | Soviet Union |
| Manufacturer | NPO AL, Salyut, Perm PMZ, OMKB, UMPO, MMP Chern |
| Major applications | |
Design and development
The AL-21 is closely similar in technology to the General Electric J79 first flown in 1955, which was the first engine for supersonic flight, using a variable stator.[1]
It is generally described as being in the "third generation" of Soviet gas turbine engines which are characterized by high thrust-to-weight ratios and the use of turbine air cooling.[2]
The AL-21 entered service in the early 1960s. Later designed the AL-21F3, it was used in the Sukhoi Su-17, Sukhoi Su-24, Ground-attack variant Mikoyan-Gurevich MiG-23, and Sukhoi T-10 (Sukhoi Su-27 prototype).
Specifications (AL-21F3)
General characteristics
- Type: Afterburning turbojet
- Length: 5,300 mm (209 in)
- Diameter: 1,000 mm (39 in)
- Dry weight: 1,700 kg (3,740 lb)
Components
- Compressor: Two-spool 14-stage axial compressor with variable stator vanes. 10 guide vanes with rotating blades (1 inlet vane, 4 first stages, 5 last stages.
- Turbine: Two-stage high pressure, single-stage low pressure
Performance
- Maximum thrust:
- 76.4 kN (17,175 lbf) dry
- 109.8 kN (24,675 lbf) with afterburner
- Overall pressure ratio: 14.75:1
- Turbine inlet temperature: 1,100 °C (2,000 °F)
- Specific fuel consumption:
- 77.5 kg/(h·kN) (0.76 lb/(h·lbf)) at idle
- 87.7 kg/(h·kN) (0.86 lb/(h·lbf)) at maximum military power
- 189.7 kg/(h·kN) (1.86 lb/(h·lbf)) with afterburner
- Thrust-to-weight ratio: 4.6 maximum military power / 6.6 with afterburner
- Life expectancy: 1,800 hours
