Aero-engine Scientific and Technical
Complex «Soyuz»


On the AESTC «Soyuz» was created 18 base and 44 modifications turbojet engines for aircraft with a wide range of characteristics for civil and military aviation, several types of liquid rocket engines and thermal emission power installation at nuclear power for space vehicles, as well as air turbo-refrigeration installation of a new type.


Park of turbojet engines developed AESTC «Soyuz» and manufactured at factories mass-produced, amounted to more than 26000 copies, with over 60 million hours of flight operation. The aircraft with engines AESTC «Soyuz» operated in Russia in 43 countries of Europe, Asia and America. They found more than 100 world records altitude flight, rate and other records.

The most popular in the world turbojet engine at the moment of creation

In the engine compressor regulation introduced by restart air for the first stage. The engine has axial eight-stage compressor with subsonic high-pressure stages. Apply on-board automatic launching of turbine starter C-300M through fluid flywheel. The engine and its modifications set at TU-16, F-4, Tu-104.


Technical Data
Thrust 85,3 kN
Dry weight 3100 kg
Max. diameter 1,4 m
Length 5,38 m
Fuel rate 0,102 (kg/h) / N
Air mass flow 150 kg/s
Pressure ratio 6,2
The temperature gas before turbine 1130 K
Turbojet engine with the lowest unit weight in the world at the moment of creation

The engine from domestic and foreign turbo-jet engines differs lowest (more than half as much) specific thrust (0.0227 kg / N). At this engine for the first time in domestic practice, used an electric starter - a generator. The engine used on the Yak-25.


Technical Data
Thrust 19,6 kN
Dry weight 445 kg
Max. diameter 0,67 m
Length 2,77 m
Fuel rate 0,095 (kg/h) / N
Air mass flow 37,5 kg/s
Pressure ratio 5,8
The temperature gas before turbine 1130 K
The engine for the first serial supersonic fighter MIG-19 domestically produced

At the engine for the first time in domestic practice, installed the supersonic first stage compressor and used fuel - oil aggregate.


When designing the engine widely used engine experience knot finishing AM-5. The engine has nine-stage axial compressor, cannular combustion chamber, two-stage turbine, afterburner, three-position nozzle


At the engine used double-speed drive starter - generator, and used carburetor ignition afterburner.


Technical Data
Thrust 25,5 kN
Dry weight 700 kg
Max. diameter 0,665 m
Length 5,56 m
ÓFuel rate 0,095 (kg/h) / N
Air mass flow 43,3 kg/s
ÑPressure ratio 7,5
The temperature gas before turbine 1150 K
The first native twin-shaft turbojet engine with afterburning

In the engine for the first time used: twin-shaft rotor scheme, construction rotors without remote pier, fuelling an igniter with oxygen, the first time developed a twin-shaft engine regulatory principles in a wide range of flight speeds. The engine has the most massive used on aircraft MiG-21 family.


Technical Data
Thrust 49,0 kN
Dry weight 1040 kg
Max. diameter 0,825 m
Length 4,61 m
Fuel rate 0,204 (kg/h) / N
Air mass flow 64,5 kg/s
Pressure ratio 8,7
The temperature gas before turbine 1175 Ê
The first in the country engine for supersonic unmanned aerial vehigles for one-time application

The engine is a compact, has light weight, and its easy to manufacture.


Technical Data
Thrust 21,1 kN
Dry weight 380 kg
Max. diameter 0,645 m
Length 2,01 m
Fuel rate 0,133 (kg/h) / N
Air mass flow 35,5 kg/s
Pressure ratio 4,5
The temperature gas before turbine 1330 K
The engine for the installation on training and sport airplanes

The cheap and reliable engine for installation on training and sports aircraft Yak-30 and Yak-32. At the engine used seven-stage axial compressor, annular combustion chamber, single-stage turbine and unregulated jet nozzle. Modifying the engine RU19A - 300 applied as an auxiliary engine on civilian airplanes An - 24 and its modifications An - 26 and An-30. The engine is technological, has a great resource.


Technical Data
Thrust 7,96 kN
Dry weight 222 kg
Max. diameter 0,552 m
Length 1,81 m
Fuel rate 0,114 (kg/h) / N
Air mass flow 15,8 kg/s
Pressure ratio 4,43
The temperature gas before turbine 1150 K
The first native small engine for subsonic cruise missiles

The single-shaft turbofan engine. The engine has electronic automatic control system, built an electric generator capacity of 4 kW and autonomous oil system. The engine capable of screening air for aircraft.


Technical Data
Thrust 3,55 kN
Dry weight 100 kg
Max. diameter 0,315 m
Length 0,85 m
Fuel rate -
Air mass flow -
Pressure ratio -
The temperature gas before turbine -
The vectored thrust turbojet engine for the first in the world supersonic fighter vertical takeoff and landing

The turbofan engine with afterburner, with the opposite direction of rotation of rotors, with heightened gas-dynamic resistance compressors, with unique vortex burners in the main combustion chamber. For the engine developed the new turning nozzle with adjustable area nozzle throat, adjustable vectored thrust in the vertical plane on the range of 95 deg. regardless of engine regime. The engine was installed at Yak-141 on which it was established 12 world records.


Technical Data
Thrust 154 kN
Dry weight 1850 kg
Max. diameter 1,39 m
Length 4,78 m
Bypass ratio 0,81
Fuel rate 0,169 (kg/h) / N
Air mass flow 180 kg/s
Pressure ratio 22
The temperature gas before turbine 1630 K
The first native vectored trusted turbojet engine

The twin-shaft engine, has curvilinear nozzle with two pivoting restrictions nozzles which are listed in the motion of two hydraulic motors with sprung sync. The engine is highly gas-dynamic resistant, even in extreme conditions with the level of uneven temperatures and pulsations pressure air inlet. The engine was installed at Yak-38.


Technical Data
Thrust 66,7 kN
Dry weight 1350 kg
Max. diameter 1,01 m
Length 3,71 m
Fuel rate 0,102 (kg/h) / N
Air mass flow 100 kg/s
Pressure ratio 10,5
The temperature gas before turbine 1440 K
The engine for the first native high-altitude supersonic fighter aircraft with a maximum speed of flifht 3000 km/h

The single-shaft turbojet engine has five-stage axial compressor, input guide apparatus, cannular combustion chamber, single-stage turbine, afterburner, three-position nozzleá automatic launching of turbine starter C-300M. For the first time duration of the flight was secured at afterburning mode. At the engine for the first time in the world has been applied electronic control regimes. Engine modifications: R15K - 300, R15BF - 300, R15BF2 - 300. On planes with engines family R15B - 300 reached more than 30 world records of speed, altitude and rate. Implemented by plane MiG-25 and its modifications.


Technical Data
Thrust 109,8 kN
Dry weight 2590 kg
Max. diameter 1,64 m
Length 6,65 m
Fuel rate 0,270 (kg/h) / N
Air mass flow 144 kg/s
Pressure ratio 4,75
The temperature gas before turbine 1230 K
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