Shvetsov ASh-62

The Shvetsov ASh-62 (Russian: АШ-62, designated M-62 before 1941) is a nine-cylinder, air-cooled, radial aircraft engine produced in the Soviet Union. A version of this engine is produced in Poland as the ASz-62 and the People's Republic of China as the HS-5.

ASh-62
Shvetsov ASh-62 installed in a Lisunov Li-2 (Cowling removed).
Type Radial engine
Manufacturer Shvetsov
First run 1937
Major applications Antonov An-2, Polikarpov I-153, Polikarpov I-16, Lisunov Li-2
Number built 40,631
Developed from Shvetsov M-25
Developed into Shvetsov ASh-82

Design and development

The ASh-62 was a development of the Wright R-1820 Cyclone that had been built in Russia under licence as the Shvetsov M-25, the main improvements including a two-speed supercharger and a more efficient induction system. Power was increased from the Cyclone's 775 hp to 1,000 hp. First run in 1937, licensed versions are still in production by WSK "PZL-Kalisz" in Poland (as of 2017).[1] The Ash-62 was also produced in China. It is estimated that 40,361 were produced in the USSR.

Polish-built ASz-62IR engines (Polish transcription of Russian name), by WSK "PZL-Kalisz" in Kalisz, are compatible with FAR-33 requirements. Further developments in Poland are the K9-AA, K9-BA and K9-BB engines, with take-off power of 1178 hp (860 kW), indicated power 698 kW. From 2015 the ASz-62IR-16E was produced with electronic fuel injection, offering greater power and the possibility of running on commercial automotive fuel.[1]

The M-63 was an improved version of the M-62 with the power output increased to 821 kW (1,100 hp) at 2,300 rpm for takeoff and 671 kW (900 hp) at 2,200 rpm at 4,500 m (14,764 ft) due to a higher compression ratio of 7.2:1 and a higher redline.

Applications
ASz-62 installed in an Antonov An-2 (Cowling installed)

Specifications (M-62)
Family tree of Shvetsov engines

Data from Liss.[2]

General characteristics

  • Type: Nine-cylinder single-row supercharged air-cooled radial engine
  • Bore: 155.5 mm (6.122 in)
  • Stroke: 174.5 mm (6.870 in)
  • Displacement: 29.876 L (1,823.1 cu in)
  • Length: 1,213 mm (47.756 in)
  • Diameter: 1,378 mm (54.252 in)
  • Dry weight: 560 kg (1,230 lb)

Components

Performance

  • Power output: * 746 kW (1,000 hp) at 2,200 rpm for takeoff
  • 634 kW (850 hp) at 2,100 rpm at 4,200 m (13,780 ft)
  • Specific power: 25.03 kW/l (0.55 hp/in³)
  • Compression ratio: 6.4:1
  • Specific fuel consumption: 469 g/(kW•h) (0.77 lb/(hp•h))
  • Power-to-weight ratio: 1.3 kW/kg (.81 hp/lb)

See also

Related development

Related lists

References

Notes
  1. Gruszczyński, Jerzy. W pierwszej lidze dostawców, "Lotnictwo Aviation International" Nr. 9/2017, p. 34-37 (in Polish)
  2. Liss 1966, p. 9

Bibliography
  • Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 154.
  • Russian Aviation Museum
  • Venik's Aviation
  • Kotelnikov, Vladimir (2005). Russian Piston Aero Engines. Crowood Press Ltd. pp. 119–122.
  • Liss, Witold (1966). The Polikarpov I-16 (Aircraft in Profile Number 122). Profile Publications Ltd.
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