Misplaced Pages

Klimov VK-107

Article snapshot taken from Wikipedia with creative commons attribution-sharealike license. Give it a read and then ask your questions in the chat. We can research this topic together.
(Redirected from Klimov VK-107R) 1940s Soviet piston aircraft engine
VK-107
VK-107A in Central Air Force Museum (Moscow)
Type V12 engine
National origin USSR
Manufacturer Klimov
First run 1942
Major applications
Number built 7.902
Developed from M-105 and VK-106
Developed into Klimov VK-108

The Klimov VK-107 was a V-12 liquid-cooled piston aircraft engine used by Soviet aircraft during World War II.

Development

The VK-107 was developed from the M-105 and VK-106. To achieve a greater power output, each cylinder now had four valves (two intake and two exhaust), crankshaft and camshafts were completely revised, and a new supercharger design was implemented. Although the engine could have been ready for production as early as 1942, the Soviets' factories lacked the capacity to produce a brand new design. Thus, the less powerful Klimov VK-105PF and VK-105PF2 V12 engines were built instead. However, the appearance of Luftwaffe Messerschmitt Bf 109G with Daimler-Benz DB 605 engine in 1943 created an urgent demand for a more powerful engine. VK-107A was put into production in 1944 and was used on Yak-9U fighters. The engine was not well liked by either pilots or mechanics – it had a life expectancy of only 25 hours and war emergency power was almost never used for fear of decreasing this even more. The engine was also difficult to service, in part because its exhaust headers were on the inside of the cylinder banks, the reverse placement of most V-type liquid-cooled engine designs.

Variants

Data from Aircraft engines of the World 1953 and Russian piston aero engines

M-107
(M-107P) Initial designation, produced 1941-1942; 686 built.
VK-107
Prototypes with take-off rating of 1,080 kW (1,450 hp)
VK-107A
1942 production version without water-injection with military (high) rating of 1,100 kW (1,500 hp) at 2800 rpm and 4,500 m (14,800 ft), remained in production until 1948
VK-107B
with water injection
VK-107R
version for hybrid piston-motorjet powered Mikoyan-Gurevich I-250 and Sukhoi Su-5 fighters fitted with the Kholshchevnikov VRDK
VK-107 coupled
A projected coupled powerplant driving contra-rotating propellers
VK-108
attempt to further develop VK-107 with a rating of 1,380 kW (1,850 hp) for takeoff, used on several Yakovlev Yak-3 and Myasishchev DB-108 prototypes but did not enter production.
VK-108F
Boosted VK-108
VK-109
1945-6 development of the VK-108, planned for use on the Myasishchev VB-109 bomber.

Applications

Specifications (VK-107B)

Data from Aircraft engines of the World 1953

General characteristics

  • Type: 12-cylinder supercharged liquid-cooled Vee aircraft piston engine
  • Bore: 148 mm (5.8 in)
  • Stroke: 170 mm (6.7 in)
  • Displacement: 35.08 L (2,141 cu in)
  • Length: 2,030 mm (80 in)
  • Width: 777 mm (30.6 in)
  • Height: 960 mm (38 in)
  • Dry weight: 620 kg (1,370 lb)
  • Power boost:Water injection for take-off and combat boost

Components

  • Valvetrain: Two intake and two exhaust valves per cylinder actuated via an overhead camshaft
  • Supercharger: Single stage, two-speed, gear-driven centrifugal type supercharger with variable output impeller driven at 7.85:1 and 10:1.
  • Fuel system: 6x K-105BP carburettors with automatic pressure regulation
  • Fuel type: 95 Octane
  • Oil system: Pressure feed at 5.9 bar (85 psi), Oil viscosity 20.5 centistokes (0.03177506355013 in/s)
  • Cooling system: Liquid-cooled
  • Reduction gear: Spur gear 0.6:1 with hollow propeller shaft for cannon

Performance

  • Power output: Take-off (wet): 1,300 kW (1,800 hp) at 2,800 rpm / 53.1 in (1,350 mm) / +11.6 lb (5.3 kg) boost
Take-off (dry): 1,200 kW (1,600 hp) at 2,800 rpm / 52.4 in (1,330 mm) / +11.2 lb (5.1 kg) boost
Military (low): 1,200 kW (1,600 hp) at 2,800 rpm / 1,700 m (5,600 ft) altitude
Military (high): 1,100 kW (1,500 hp) at 2,800 rpm / 6,000 m (19,700 ft) altitude
Normal (low): 1,110 kW (1,490 hp) at 2,600 rpm / 2,000 m (6,600 ft) altitude
Normal (high): 1,010 kW (1,350 hp) at 2,600 rpm / 5,000 m (16,400 ft) altitude

See also

Related development

Comparable engines

Related lists

References

  1. Gunston 1989, p.90.
  2. Kotelnikov 2005, p. 143.
  3. ^ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 315.
  4. Kotelnikov, Vladimir (2005). Russian piston aero engines. Ramsbury, Wlits: Crowood. pp. 134, 142–143, 145, 183–184, 254. ISBN 1-86126-702-9.

Bibliography

  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
  • Kotelnikov, Vladimir. Russian Piston Aero Engines. Marlborough, Wiltshire. The Crowood Press Ltd. 2005. ISBN 1-86126-702-9.
Klimov aircraft engines
Piston engines
Turbojets
TurbofansRD-33
Turboprops and turboshafts
Categories: