Klimov VK-1
The Klimov WK -1 was a Soviet turbojet. It was the first Soviet jet engine, which was manufactured in large series. The letters of the name are the initials of the designer Vladimir Klimov.
It was a further development of the Klimov RD -45 and based in the UK as this Rolls- Royce Nene engine, however, had an increase of about 30 percent thrust as the output pattern without the external dimensions were enlarged.
It is a Einwellentriebwerk with a single-stage centrifugal compressor, had two inlets. The combustion air was passed through nine individual combustion chambers for single-stage turbine. The aviation approval was granted in December 1948. It was used in the Mikoyan -Gurevich MiG- 15bis. A variant WK -1A with a modified gearbox and better durability solved the original engine from series production and was used in the patterns of the Mikoyan -Gurevich MiG -17, the Ilyushin Il- 28 and Tupolev Tu -14. A version with an afterburner, as WK -1F ( Forsasch ) denotes, was produced in 1951 and came in later versions of the MiG -17 ( F, PF and R ) are used. In addition, however, also found in other aircraft use. The engine was manufactured in Poland, Czechoslovakia and China. There, the production ran until 1958. Were produced more than 20,000 units.
The Klimov WK -5 was an evolution of WK -1 with increased turbine inlet temperature and greater thrust. This engine was created in 1952 and was admitted in the variant WK- 5F also equipped with an afterburner. However, it was not widespread. The engine delivered a thrust of 30.4 kN, 37.3 kN with afterburner.
After the end of their use as an aircraft engine a number of WK -1 engines was fed to other uses, such as Eisabtaugeräte for airfield drying or turbo extinguishers.
Since the engine on the Rolls -Royce Nene based and it was built without a license contract in series, Rolls-Royce later attempted to sue for 207 million pounds royalties, thus remained without success.
Technical data ( WK -1A )
- Length: 2640 mm
- Diameter: 1270 mm
- Weight: 872 kg
- Takeoff thrust 26.5 kN (WK -1F with afterburner: 33.16 kN)
- Specific fuel consumption: 109.1 kg / (kN h)
- Turbine speed: 11,560 min-1