Klimow RD-33
The Klimow RD-33 ( Russian Климов РД-33 ) is a turbofan engine from the Russian company Klimow . It was developed from the early 1970s and is used as a drive for the MiG-29 fighter aircraft . The first flight of a prototype in a test aircraft took place on April 20, 1978, the first flight in a MiG-29 on December 30, 1979. Series production then began in 1980.
It is a twin-shaft engine with an adjustable afterburner and a thrust range of 50 to 80 kN. Important features are the modular structure (individual parts can be exchanged separately) and the high reliability even under operating conditions.
variants
After years of development and use, the engine has grown into a family of different models. A thrust vector control and digital diagnosis, control and monitoring systems are available in current models .
- RD-33 : Basic model, developed from 1985 for the MiG-29.
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RD-33 Series 3 : revised model with a longer service life , which is used in new or rebuilt old versions of the MiG-29, such as the MiG-29 and MiG-29SMT.
In 2005, Russia signed a $ 250 million contract with India to modernize the Indian Air Force's MiG-29s , with 120 of these engines to be built under license by Hindustan Aeronautics Ltd. Later, the plant will also take on the assembly of the RD-33MK for the MiG-29K of the Indian aircraft carrier Vikramaditya .
- RD-33B / NB : Variant without afterburner for different types of aircraft.
- SMR-95 : A variant for modernizing second and third generation foreign jets. 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 as a drive for the JF-17 / FC-1 . According to JF-17.com, "the most significant difference is the repositioning of the gearbox on the underside of the engine casing".
- RD-33MK : The RD-33MK "Morskaja Osa" (Russian: Морская Оса , German: Seewespe ) is the latest model in the family. It was developed in 2001 as a drive for the aircraft carrier variants MiG-29K and MiG-29KUB, but was also adapted to the MiG-35 . Compared to the basic model, the new engine has 7% more thrust, which is due to the use of modern materials for the cooled blades and thus a 40 K higher combustion chamber temperature. The length and maximum diameter remain the same, while the afterburner thrust and dry weight (to 1145 kg) increase. It also contains systems (for example new combustion chambers) that are designed to reduce visibility in the infrared and optical range. The service life increased to 4000 hours and the performance at high outside temperatures was also improved.
Technical data (RD-33)
general characteristics
- Type: Afterburner - Turbofan
- Length: 4.229 m
- Diameter:
- Air inlet: 0.73 m
- maximum: 1.00 m
- Empty weight: 1055 kg (complete drive system: 1217 kg)
Components
- Compressor : Two-shaft axial compressor with nine high-pressure and four low-pressure compressor stages and a two-stage inlet guide device
- Turbine : one high and one low pressure turbine stage with coated single crystal blades
- Combustion chamber : annular combustion chamber with 24 injection nozzles
- Starter : mechanically coupled via APU
power
- Thrust: 49.4 kN without, 81.3 kN with afterburner
- Total print ratio: 20: 1
- Turbine inlet temperature: 1407 ° C
- Bypass ratio : 0.49: 1
- Specific fuel consumption:
- 75 kg / (kN · h) military thrust
- 188 kg / (kN · h) with afterburner
- Oil consumption: 0.8 kg / h
- Thrust-to-weight ratio: 77.1 N / kg (7.9: 1)
- Response time: 4 s from idling to full afterburner use
Sources: Klimow; RD-33 reference data
| Other data of the RD-33 | |
| Inside diameter | 730 mm |
| Air throughput at max. thrust | 76 kg / s |
| specific weight | 0.127 |
| Thrust-to-weight ratio dry / built-in | 7.47: 1 / 5.53: 1 |
| Top speed | 2.35 Mach at high altitude |
| Service ceiling | 17,069 m |
| Idle fuel consumption | 350 kg / h |
| Max. Fuel consumption with afterburner at sea level | 68,184 kg / h |
| Max. Fuel consumption with afterburner at an altitude of 9100 m | 19.092 kg / h |
| Max. Turbine inlet temperature at sea level / high altitude | 1530 K / 1680 K |
| Turbine speeds at maximum thrust (high / low pressure turbine) | 15,500 / 11,000 rpm |
Source: Klimow website, as shown below.
See also
Web links
Commons : Klimow RD-33 - Collection of Images
- Klimow's official website for the RD-33 turbojet engine family
- Official website of the RD-33MK
- Official website of the thrust vector variant
- Official website of the SMR-95
Individual evidence
- ↑ Data sheet at Flugzeugtechnik.info ( Memento of the original from February 18, 2014 in the Internet Archive ) Info: The archive link was inserted automatically and has not yet been checked. Please check the original and archive link according to the instructions and then remove this notice.
- ↑ Data sheet on the homepage of Wolfgang Bredow
- ↑ Report on the German MiG-29 (English) ( Memento of the original from September 25, 2006 in the Internet Archive ) Info: The archive link was inserted automatically and has not yet been checked. Please check the original and archive link according to the instructions and then remove this notice.
