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AL-21F-3 Turbojet Engine

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The AL-21F-3 engine features a single-shaft configuration. The 14-stage compressor has a sophisticated control system. The cannular combustion chamber has 12 flame tubes. The three-stage turbine is of an impulse-reaction type. The blades of the first and second turbine stages are cooled with the bleed air taken from the compressor. The afterburner has three annular stabilisers and six fuel manifolds with spray and swirl-type nozzles. A perforated screen is installed to ensure internal cooling. The fully variable area propelling nozzle consists of the subsonic convergent and supersonic divergent rims.

Thrust (H=0, M=0, ISA), kgf:

max continuous 7,800

min afterburner 9,700

full afterburner 11,250

 

Specific fuel consumption, kg/kgf/h:

economy power (H=0, M=0) 0.80

cruising mode 0.76

max continuous 1.86

 

Air consumption, kg/sec

104

 

Pressure ratio

14.55

 

Gas temperature before the turbine, oK

1,385

 

Dimensions, mm:

length /diameter 5,340/1,030

 

Engine dry weight, kg

1,800

Defense Products & Services: AL-21F-3 Turbojet Engine
Companies & Organizations: 
Defense Products & Services Sectors: Turbojet / turbofan engines, aircraft
Description: AL-21F-3 Turbojet Engine
Source of Information: Rosoboronexport Joint Stock Company