The Kuznetsov NK-6 was a low-bypass afterburning turbofan engine, designed by the Kuznetsov Design Bureau.

Development

Development of the NK-6 started in 1955 at the Kuznetsov Design Bureau.[2] It was the first afterburning by-pass engine made in the Soviet Union.[1] With a maximum thrust of 216 kN (49,000 lbf), it was the most powerful jet engine in the world in the early 1960s.[2] Despite this fact, development of the NK-6 was halted in July 1963.[2] The accumulated experience of the NK-6 project was subsequently used in the development of the NK-144.[2]

A modified version of this engine, the NK-7, was intended for the Soviet Navy[1] and had a takeoff thrust of 216 kN (49,000 lbf).

Applications

• Project "106"[3] (proposed)
• Tupolev Tu-95LL (testbed)
• Tupolev Tu-123[4] (proposed)
• Tupolev Tu-125[1] (proposed)
• Tupolev Tu-135[3] (proposed)

Specifications (NK-6)

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

General characteristics

• Type: Two-spool low-bypass afterburning turbofan
• Length: 4,810 mm (189 in)
• Diameter: 1,750 mm (69 in)
• Dry weight: 3,200 kg (7,100 lb)

Components

• Compressor: 4-stage LP,[1] 6-stage HP[1]
• Combustors: Annular multi-nozzle combustion chamber[1]
• Turbine: 1-stage HP,[1] 2-stage LP[1]

Performance

• Maximum thrust:
  
  • 216 kN (49,000 lbf)[1] at takeoff
  • 196.2 kN (44,100 lbf)[1] in cruise with afterburner
  • 34.3 kN (7,700 lbf)[1] in cruise without afterburner
• Overall pressure ratio: 13.4[1] at takeoff
• Bypass ratio: 1.79[1]
• Air mass flow: 343 kg/s (760 lb/s)[1]
• Turbine inlet temperature: 1,400 K (1,130 °C; 2,060 °F)[1]
• Specific fuel consumption:
  
  • 183.6 kg/(kN⋅h)[1] at takeoff
  • 200 kg/(kN⋅h)[1] in cruise with afterburner
  • 87.7 kg/(kN⋅h)[1] in cruise without afterburner
• Power-to-weight ratio:

See also

Comparable engines

• Kuznetsov NK-22

Related lists

• List of aircraft engines

References

На других языках

[ru] НК-6