| AL-21 | |
|---|---|
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| Lyulka AL-21F3 engine, Airforce Museum of the Bundeswehr; Berlin-Gatow |
The Lyulka AL-21 is an axial flow turbojet engine created by the Soviet Design Bureau named for its chief designer Arkhip Mikhailovich Lyulka.
Design and development[]
The AL-21 entered service in the early 1960s. With later marks AL-21F3 it was used in the Sukhoi Su-17, Sukhoi Su-24, early Mikoyan-Gurevich MiG-23, and Sukhoi T-10 (Sukhoi Su-27 prototype). A non-afterburning version powered the Yakovlev Yak-38 VTOL fighter.
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: 14-stage axial compressor with variable stator blades
- 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: 64.7 N/kg (6.6:1)
References[]
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The original article can be found at Lyulka AL-21 and the edit history here.