RD-33 is a twin-shaft twin-turbo turbojet with afterburner chamber (TRDDF), developed in 1968-1985 at Klimov OJSC under the supervision of S. P. Izotov and V. V. Starovoitenkov. About 5,000 RD-33 engines were produced. The most massive dual-circuit engine in its traction class.
| RD-33 | |
|---|---|
 RD-33 at the Berlin Museum | |
| Type of | Turbofan engine |
| A country |  the USSR |
| Using | |
| Years of operation | since 1977 |
| Application | MiG-29 MiG-29K MiG-35 IL-102 FC-1 / JF-17 Dassault Mirage F1 |
| Production | |
| Constructor | Klimov OJSC ( St. Petersburg ) |
| Manufacturer | Moscow Engineering Enterprise named after V.V. Chernyshev ( Moscow ) |
| Years of production | since 1977 |
| Total released | about 5000 |
| Options | RD-33I RD-33K RD-33 Series 3 RD-33 Series 3M RD-33N (SMR-95) RD-93 (afterburning, for UAV Skat) RD-33MK |
| Weight and size characteristics | |
| Dry weight | 1055 kg |
| Length | 4230 mm |
| Diameter | 1040 mm |
| Performance data | |
| Thrust | 5040 [1] kgf |
| Afterburner rod | 8300 [1] kgf |
| Compressor | KND / fan - axial 4-speed., KVD - axial 9-speed. with a controlled input device and the first two stages of the stator |
| Turbine | TVD - axial 1-speed., TND - axial 1-speed., Cooled |
| Turbine temperature | 1260-1265 ° C |
| The combustion chamber | straight-through ring |
| Degree of pressure increase | 21.7 |
| Air flow | 76.5-77 kg / s |
| Specific fuel consumption | 0.77 (In the maximum afterburning mode) kg / kgf · h |
| Bypass Degree | 0.55 |
| Specific thrust | 7.86 kgf / kg |
The estimated cost of one RD-33 engine (as of 2008 ) is 68.3 million rubles [2] .
Content
History
The design of the RD-33 engine began in 1968, bench tests took place in 1972, mass deliveries began in 1981, state tests of the engine were completed in 1984, and adoption was adopted in 1985.
RD-33MK (GSI 2012) is a modification of the RD-33 engine, which has improved characteristics: the assigned service life is increased to 4000 hours, thrust is increased by 7% due to the increase in gas temperature in front of the turbine, it is equipped with the FADEC system, which has been developed since 2001.
Design
Dual-circuit engine with 4 stages of low pressure fuel pump, 9 stages of high pressure fuel pump, short annular combustion chamber with 24 nozzles, single-stage high pressure fuel pump and high pressure fuel pump (single-crystal), afterburner. The control system is electro-hydromechanical. The gas temperature in front of the turbine is 1680 K. The engine can work in any spatial position of the aircraft.
Media
The engine is intended for the light front-line fighter MiG-29 and other aircraft of this class. RD-33 and its modifications are installed on fighter MiG-29 (RD-33 series 2), MiG-29K (RD-33K), MiG-35 (RD-33MK), Super Mirage F-1, Super Cheetah D-2 ( both - RD-33N (СМР-95)). Also, the modification of the RD-33I engine was installed on an experimental Il-102 attack aircraft .
Modifications
RD-33I (I-88)
Modification of the engine without afterburner for an experienced Il-102 attack aircraft .
RD-33K
Modification for the MiG-29K deck-based and upgraded MiG-29M.
| Technical characteristics of the RD-33K engine | |
|---|---|
| Emergency take-off thrust: | 9 400 kgf |
| Afterburner thrust: | 8 800 kgf |
| Maximum thrust draft: | 5 400 kgf |
RD-33 Series 2
Modification with the assigned resource increased to 1400 hours.
RD-33 Series 3
Modification with the assigned resource increased to 2000 hours. It has been mass-produced since 1999 .
RD-33 3M Series
Modification for the deck fighter MiG-29K. An emergency take-off mode with a thrust of 8700 kgf was introduced, and structural changes were also made.
RD-33B / NB
Engines without afterburner for aircraft for various purposes.
RD-33N (SMR-95)
Modification with the lower arrangement of the box of engine units for the modernization of fighters Super Mirage F-1 and Super Cheetah D-2 South African Air Force . The first Russian project to create a turbojet engine for a foreign fighter. Thanks to the replacement of standard engines with SMR-95 LTX engines, the effectiveness of combat aircraft use increased by 1.2 to 3 times.
RD-93
Modification with the lower arrangement of the box of propulsion units for the Chinese light fighter FC-1 . Specifications correspond to RD-33.
RD-33MK
RD-33MK Marine Wasp is an upgraded version of the RD-33 engine. Afterburner traction increased to 9000 kgf . It is installed on the latest MiG-29K, MiG-29KUB, MiG-35 fighters , the gearbox is located on top.
Specifications:
- Length 4229 mm
- Diameter 1040 mm
- Weight 1055 kg
- Afterburner 9000 kgf
- Maximum 5400 kgf
- Resource 4000/1000 hours
- Air consumption 82 kg / s
- Compression ratio 24
Modification of the RD-33 with a deflected thrust vector
Modification for the pilot fighter MiG-29M / OVT. The technology by which the nozzle with a deflected thrust vector is designed is universal. This allows you to install a deflectable nozzle on turbojet engines of various designs, both Russian and foreign production.
The nozzle design, made according to the axisymmetric scheme with the rotation of the supersonic part, provides the possibility of a foreshortened change in the thrust vector, the greatest angular velocity of its deviation and the smallest increase in engine mass. The thrust vector is rejected by changing the position of the valves of the multimode nozzle by a predetermined angle.
The maximum deviation of the nozzle from the longitudinal axis is 15 degrees with a rotation speed of 60 degrees / s, which gives a significant increase in maneuverability and improves flight characteristics at supercritical angles.
Notes
- ↑ 1 2 At Н = 0, V = 0, Тn = + 15 ° С
- ↑ Official site of the Russian Federation for placing information on placing orders (inaccessible link)
Literature
- Zrelov V. A. Domestic gas turbine engines. The main parameters and design schemes. - Engineering, 2005 .-- S. 196-207, 223. - 336 p. - (For universities). - ISBN 5-217-03254-5 .
Links
- Engines of the RD-33 family , Klimov OJSC
- RD-33MK , Klimov OJSC
- RD-33 , LeteckeMotory.cz (Czech)