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R25-300 Turbojet Engine

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The R25-300 two-shaft, two-rotor engine with afterburner has a three-stage low-pressure compressor and a five-stage high-pressure compressor, a cannular combustion chamber, single-staged low- and high-pressure turbines, and a fixed-area nozzle. The two-stage afterburner allows high-altitude air combat.

 

The engine’s main advantages are convenient maintenance, a continuous range of afterburning modes control with smooth thrust change, and easy single-handle control. The engine has two afterburning modes: afterburner and emergency thrust. The engine is designed to power the MiG-21 family aircraft. The R25-300-94 is designed to power the MiG-21-93 aircraft. It has an integrated hydroblade drive generator with multiplier and a reinforced gearbox drive chain.

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

emergency thrust 7,100*

afterburner 6,850

 

Specific fuel consumption, kg/kgf/h

0.91

 

Air consumption, kg/sec

68.5

 

Pressure ratio

9.1

 

Gas temperature before the turbine, oK

1,353

 

Dimensions, mm:

length 4,615

max diameter 907

 

Engine dry weight, kg 1,215

* - 9,900 kgf at M=1.0

Defense Products & Services: R25-300 Turbojet Engine
Companies & Organizations: 
Defense Products & Services Sectors: Turbojet / turbofan engines, aircraft
Description: R25-300 Turbojet Engine
Source of Information: Rosoboronexport Joint Stock Company