Lyulka AL-21

The Ljulka AL -21 is a jet engine, which was developed in the USSR of archip Mikhailovich Ljulka and developed from the early 1960s as the successor of the AL -7 and manufactured from 1967 in large series.

In the standard version AL -21F -3 is a single-shaft turbojet engine with a 14 -stage axial compressor with vanes that were adjustable in 1 to 4 and 10 to 14 stage. The turbine blades of the first two stages of the three -stage turbine were cooled by the compressor bleed air. The combustion chamber was a pipe - annular combustor with 12 nozzles.

AL -21 versions

  • AL -21F - version of the Tu -128
  • AL -21F- 3 - version from 1970 for the MiG -23B, Su -22 and Su- 24 and T-10 and Su -17
  • AL -21F -3A - version of Su- 17M and Su -24M

Specifications

  • Takeoff thrust with afterburner: 110 kN
  • Takeoff thrust without afterburner: 76.5 kN
  • Max. Speed: 11.150/min
  • Turbine inlet temperature of 1370 ° C
  • Max. Air flow rate 104 kg / s
  • Compression: 14,75:1
  • Weight (dry ): 1800 kg ( 1580 kg for Al -21F )
  • Diameter: 1.03 m
  • Length: 5.34 m
Sukhoi Su-22 Sukhoi Su-17 Saturn AL-41 PowerJet SaM146
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