Klimov RD-33

The Klimov RD -33 turbofan engine is a Russian company Klimov. It was developed from the beginning of the 1970s, and came as a drive for the fighter aircraft MiG -29 is used. The first flight of a prototype in a test aircraft took place on 20 April 1978 the first flight in a MiG -29 on 30 December 1979. Serial production began in 1980 ..

It is a two shaft engine with an adjustable burner and the thrust range of 50 to 80 kN. Important features are the modular structure ( individual parts can be replaced separately ) and the high reliability even under conditions of use.

Variants

After years of development and use, the engine has developed a family of different models. Thus, a thrust vector control and digital diagnosis, control and monitoring systems are available at other at current models.

  • RD -33: basic model, developed from 1985 for the MiG - 29th
  • RD -33 series 3: revised model with a longer life, including for use on new or rebuilt old variants of the MiG- 29 as the MiG- 29 and MiG- 29SMT. In 2005, Russia signed a contract worth 250 million dollars with India to modernize the MiG- 29 of the Indian Air Force, with 120 pieces of these engines will be built at Hindustan Aeronautics Ltd under license. Later intended to take over the installation of the RD- 33MK for the MiG - 29K of the Indian aircraft carrier Vikramaditya the work.
  • RD-33B/NB: Version without afterburner for different aircraft types.
  • SMR 95: A variant for the modernization of foreign jets of the second and third generation. The engine successfully completed ground and flight tests in the Dassault Mirage F1 and Super Cheetah D -2 of the South African Air Force.
  • RD -93: Variant, planned as a drive for the JF-17/FC-1. According to JF- 17.com is " the most significant difference is the repositioning of the gear at the bottom of the casing of the engine ."
  • RD- 33MK: The RD- 33MK " Morskaja Osa " (Russian: Морская Оса, German: sea wasp ) is the latest model of the family. It was developed as a drive for the aircraft carrier variant MiG- 29K and MiG- 29KUB in 2001, but has been adapted to the MiG -35. The new engine has 7 % more thrust compared to the base model, which is due to the use of modern materials in the cooled blades, which is 40 ° C higher combustion chamber temperature. The length and the maximum diameter remains the same while the Nachbrennerschub and the dry weight ( at 1145 kg) to enlarge. It also contains systems ( such as new combustion chambers ), which are intended to reduce the visibility in the infrared and optical range. The lifetime increased to 4000 hours, the performance at high ambient temperatures has also been improved.

Technical data (RD -33)

General features

  • Type: afterburner turbofan
  • Length: 4,229 m
  • Diameter: Air inlet: 0.73 m
  • Maximum: 1.00 m

Components

  • Compressor: two-shaft axial compressor with nine high-pressure and four low pressure compressor stages and two-stage Vorleitapparat
  • Turbine: one high - and low-pressure turbine stage with coated Einkristallschaufeln
  • Burner: annular combustor with 24 fuel injectors
  • Starter: mechanically coupled via APU

Performance

  • Thrust: 49.4 kN without, 81.3 kN with afterburner
  • Overall pressure ratio: 20:1
  • Turbine inlet temperature: 1953 ° C
  • Bypass ratio: 0.49:1
  • Specific fuel consumption: 7.5 kg / (kN · h) military thrust
  • 20.1 kg / (kN · h) with afterburner

Sources: Klimov; Phoenix Open Source Flight Simulator, RD -33 Reference Data

Source: Website Klimov, as shown below.

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