Production

19
July
 2018

 

RD-33 turbofan twin-shift engine with afterburner for the duel-engine power plant for Mikoyan MiG-29 fighter with individual supersonic variable intake for each engine.  http://www.tmkb-soyuz.ru/assets/images/rd-33.gif

The engine was designed and produced by the Klimov company led by Designer General   S. P. Izotov in 1982; The P. I. Baranov Central Institute of Aviation Motor Development fulfilled its creation, production and development. This Institute fully calculated turbine, conducted different calculations of combustion chamber, afterburner, other engine mounts, gave guidelines and further assisted during the engine’s development, design and production. Numerous tests of engine’s gas-generator, turbine, compressor, combustion chamber and other mounts were conducted during engine design and  development on the Institute test facilities. RD-33 combustion chamber and fully variable nozzle for Mikoyan MiG-29 fighter were designed by Turaevo Machine-building Design Bureau “SOYUZ”. State bed tests were conducted in the end of 1984 under the direction of Design General V.G. Stepanov in coordination with Chernyshev Moscow Machine-Building Enterprise and Tushino Machine-building Design Bureau “SOYUZ”.  At the same time Turaevo Machine-building Design Bureau and design managers K.R.Khachaturov, Yu.V.Shvetsov, R.Yu.Nusberg worked on the engine development. A.A. Sarkisov was the Designer General. This development helped to design and implement a lot of technological and methodological concepts which allowed to increase durability and necessary reliability both of particular engine mounts and the whole engine. The number of design concepts received patents. As a result, engine resource was increased in several times. The engine has module construction and consists of 9 modules. The engine possesses 4-stage low pressure axis-flow compressor, nine-stage high pressure compressor, annular straight flow combustion chamber with 24 burners, single-stage cooled high load turbines of low and high pressure, variable nozzle afterburner, modern electric-hydromechanical control system. The engine works reliable on the ground and during flight; on the ground at a temperature of 60 oC, in the air with engine inlet temperature no more than 200  oC; at maximal indicated speed till altitude of 11 km – 1500 km/h; at maximal mach number at altitude more than 11 km – 2,35; at minimal indicated speed at altitude more than 15 km – 350 km/h, static ceiling at maximal designed altitude at actual speed of more than 1700 km/h – no less than 20 km; dynamic ceiling is higher than static one on 1,5 km. The engine works stably in extreme conditions on distortion levels and inlet air ripple. Afterburner’s and variable nozzle’s constructions firstly implemented such design concepts as: carbureted afterburner fuel supply, that provides increased afterburner’s combustion stability; the use of numerous cast thin-walled details made of heat-resisting alloys and titanium which allowed to minimize engine’s gross weight.

 

Klimov RD-33 engine. Technical specifications

Full afterburning performance (Н=0, Мп=0, МСА):

Thrust, kgf

Specific fuel consumption, kg/kgf-sec

 

8300

2,05...2,01

Maximum performance without afterburning (Н=0, Мп=0, МСА):

Specific impulse/thrust, kgf

Specific fuel consumption, kg/kgf-sec

 

5040

0,77

Bypass ratio

0,46

Total compression ratio

21

Maximal turbine inlet temperature, K

1680

Dimensions, mm:

Maximal diameter

Length

 

1040

4230

Weight, kg

1055

 

Mass production: since 1985 by the Chernyshev Moscow Machine-Building Enterprise and the P. I. Baranov Central Institute of Aviation Motor Development. The total number of produced RD-33 engines is more than 5000.

Overhaul can be done in the Chernyshev Moscow Machine-Building Enterprise.

This engine is installed on Mikoyan MiG-29 fighter or its modifications.

Modifications:

RD-33 series 3

Revised model with a longer service life

Intended for MiG-29 fighter and its modifications

 

RD-33K

Revised model with increased air flow

This modification differs from original model in low-pressure spool, modified fuel equipment and electronic digital control system.  

RD-33K engine. Technical specifications

Full afterburning performance (Н=0, Мп=0, МСА):

Thrust, kgf

8800

Maximum performance without afterburning (Н=0, Мп=0, МСА):

Specific impulse/thrust, kgf

Specific fuel consumption, kg/kgf-sec

 

5500

0,77

Dimensions, mm:

Maximal diameter

Lenght

 

1040

4230

Weight, kg

1055

 

This engine is installed on MiG-29K.

 

SMR-95

 

Revised model with accessory gearbox repositioned below the engine.

 

RD-93 - A variant with the repositioning of the gearbox along the bottom of the engine casing.

 

It’s currently under development.

RD-133  http://www.tmkb-soyuz.ru/assets/images/RD-133.jpg

Revised model with thrust vectoring nozzle.

 

RD-133 engineTechnical specifications

 

Full afterburning performance (Н=0, Мп=0, МСА):

Specific impulse/thrust, kgf

8300

Maximum performance without afterburning (Н=0, Мп=0, МСА):

Specific impulse/thrust, kgf

Specific fuel consumption, kg/kgf-sec

 

 

5040

0.77

Dimensions, mm:

Maximal diameter

Length

 

1040

4230

Weight, kg

1145

Thrust vector deflection of jet nozzle in any direction

+15о

 

It’s intended for MiG-29 fighter.

http://www.tmkb-soyuz.ru/assets/images/mig-29j.jpg

 

 Here, we used the following materials:

1. Site "Klimov Plant Named" www.klimov.ru

2. "Engines 1944-2000: aircraft, missile, marine and industrial." Illustrated electronic reference book. The third edition, revised and enlarged. Publishing company "AKS-Konversalt", 2000

3."Aircraft engine: Encyclopedia" / general editing and preface Professor V. Chujko. - M. Ed. House "Aviamir", 1999

4. Site. www.sonbi.ru