Soloviev D-20

The Soloviev D-20P, built by the Soloviev Design Bureau, was a low-bypass turbofan engine rated at 52.9 kN (11,900 lbf) thrust used on the Tupolev Tu-124. A later derivative with increased bypass ratio, the D-20P-125, was developed into the Soloviev D-30 family of low and medium bypass engines.[1]

D-20
Left side view of the Soloviev D-20 engine
Type	Turbofan
Manufacturer	Soloviev Design Bureau
Major applications	Tupolev Tu-124

Specifications

Data from Aircraft engines of the World 1970[2]

General characteristics

• Type: Twin-spool turbofan engine
• Length: 3,304 mm (130.1 in)
• Diameter: 976 mm (38.4 in)
  
• Frontal area: 0.74 m² (8 sq ft)
• Dry weight: 1,450 kg (3,200 lb)

Components

• Compressor: Three-stage LP, eight-stage HP, axial flow
• Combustors: Cannular with 12 flame tubes
• Turbine: Two-stage LP turbine, single-stage HP turbine
• Fuel type: Aviation Kerosene, Jet A, Jet A-1, JP-1
• Oil system: Pressure spray at 3.9 bar (57 psi)

Performance

• Maximum thrust: 53 kN (11,900 lbf) at 11,700 HP rpm
• Overall pressure ratio: 13:1 overall
  

• Fan pressure ratio: 2.6:1
  
• HP pressure ratio: 13.6:1

• Bypass ratio: 1:1
• Air mass flow:
  

• Fan mass airflow: 113 kg/s (250 lb/s) at 8,550 LP rpm
  
• HP mass airflow: 56.5 kg/s (125 lb/s) at 11,7000 HP rpm

• Turbine inlet temperature: JPT 923 K (650 °C)
• Specific fuel consumption:
  

• S.f.c. cruise: 73 kg/kN/h (0.72 lb/lbf/h)
  
• S.f.c. take-off: 92 kg/kN/h (0.9 lb/lbf/h)

• Thrust-to-weight ratio: 3.73

See also

Related lists

• List of aircraft engines

References

1. Gunston, Bill (1989). World Encyclopaedia of Aero Engines (2nd ed.). Cambridge, England: Patrick Stephens Limited. p. 164. ISBN 978-1-85260-163-8.
2. Wilkinson, Paul H. (1970). Aircraft engines of the World 1970 (22nd ed.). London: Paul H. Wilkinson. p. 223.

Further reading

• Taylor, John W.R., ed. (1972). Jane's all the World's Aircraft 1972–73. London: Sampson Low, Marston & Co. Ltd. p. 751. ISBN 978-0354001090.