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Soloviev D 20

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The Soloviev D-20P was a low-bypass turbofan engine rated at 52.9 kN (11,900 lbf) thrust. It was built by the Soloviev Design Bureau. The engine was used on the Tupolev Tu-124.

Contents

Specifications

Data from Gunston and Jane's.

General characteristics

  • Type: Twin-spool turbofan engine
  • Length: 330.4 cm (130 in)
  • Diameter: 97.6 cm (38.3 in)
  • Dry weight: 1,468 kg (3,236 lb)

    • Components

  • Compressor: Three-stage LP, eight-stage HP, axial flow
  • Combustors: 12-chamber cannular
  • Turbine: Two-stage LP turbine, single-stage HP turbine
  • Fuel type: Avtur

    • Performance

  • Maximum thrust: 5,400 kg (11,905 lb)
  • Overall pressure ratio: 13:1
  • Bypass ratio: 1:1
  • Air mass flow: 113 kg/s (249 lb/s) at 8,550 rpm
  • Specific fuel consumption: 0.72 (Max take-off) 0.9 (cruise)
  • Power-to-weight ratio:

    • References

    Soloviev D-20 Wikipedia
    (Text) CC BY-SA


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