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R-95Sh, R-195 Turbojet Engines

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The R-95Sh and R-195 engines feature a two-shaft configuration and a modular design. There is a three-stage low-pressure compressor without a guide vane, and a five-stage high-pressure compressor. The cannular combustion chamber has twin nozzles. The lowand high-pressure turbines are single-staged. There is no afterburner, and the nozzle is of a fixed-area type.

 

The engines are noted for ease of operation, high reliability and combat survivability. They can withstand 23mm round hits, and retain operability after considerable damage (combat proven cases). The R-195 engine is a derivative of the R-95Sh engine. It features increased thrust, improved maintainability, reduced IR signature, and enhanced stability during missile launch. The R-195 is fully interchangeable with the R- 95Sh engine.

 

Variants

The R-95Sh engine is fitted on Su-25K, Su- 25UBK, and Su-25SMK aircraft. The R-195 engine is designed for the Su-39 aircraft.

 

Basic specifications

 

R-95Sh

 

R-195

 

Thrust, kgf:

max continuous (H=0, M=0)

4,100

 

4,300

 

emergency (H=0, M=0)

4,500

Specific fuel consumption

at take-off, kg/kgf/h

0.860  

 

0.890

 

Air consumption, kg/sec

67

66

Pressure ratio

8.7

9.0

Gas temperature before the turbine, oK

 

1,148

 

1,188

Dimensions (without accessories), mm:

 

 

 

length

2,700

2,880

max diameter

772

805

Engine dry weight, kg

830

860

Defense Products & Services: R-95Sh, R-195 Turbojet Engines
Companies & Organizations: 
Defense Products & Services Sectors: Turbojet / turbofan engines, aircraft
Description: R-95Sh, R-195 Turbojet Engines
Source of Information: Rosoboronexport Joint Stock Company