The Kuznetsov NK-4 was a Soviet turboprop engine, designed by the Kuznetsov Design Bureau.

Development

Development of the NK-4 began on September 27, 1955[1] at the Kuznetsov Design Bureau. Factory tests where passed on April 17, 1956[1] and state tests where passed in 1957.[1] At the time, the NK-4 was considered an economical and technologically advanced engine.[1]

A modified version of the NK-4 that improved in terms of service life and efficiency,[1] the NK-4A, passed factory tests in October 1957.[1] State tests of the NK-4A where passed in June 1959.[1]

Applications

• Antonov An-10[1] (proposed)
• Ilyushin Il-18A[2]

Specifications (NK-4)

Data from Otechestvennaya aviatsionno-kosmicheskaya tekhnika - SAMARSKIY NTK[1]

General characteristics

• Type: Turboprop engine
• Length:
• Diameter:
• Dry weight: 970 kg (2,140 lb)[1] without propeller

Components

• Compressor:

Performance

• Maximum power output:
  
  • 2,944 kW (3,948 hp);[1] at takeoff
  • 1,580 kW (2,120 hp)[1] in cruise
• Overall pressure ratio: 7.9[1]
• Turbine inlet temperature: 1,250 K (980 °C; 1,790 °F)[1]
• Specific fuel consumption:
  
  • 0.333 kg/(kW⋅h)[1] at takeoff
  • 0.285 kg/(kW⋅h)[1] in cruise
• Power-to-weight ratio:

See also

Comparable engines

• Ivchenko AI-20

Related lists

• List of aircraft engines

References

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