RD-1700 Bypass Turbojet Engine

RD-1700 Bypass Turbojet Engine Tecnology. The RD-1700 bypass turbojet engine is designed for the MiG-UTS trainer aircraft (МiG-АТ version). The RD-1700 is a miniature bypass turbojet engine without afterburner with a fixed-area nozzle. The engine version with afterburner was also developed with the
fixed- and variable-area nozzles. The engine uses a two-shaft configuration, has a two-stage fan, a four stage high-pressure compressor and a two-stage turbine with the cooled blades. The RD-1700 Bypass Turbojet Engine is a base engine for the family of the bypass turbojet engines with a thrust of 2,000 to 3000 kgf.

RD-1700 Specifications
Maximum thrust, kgf 1,700
Specific fuel consumption, kg / (kgf.h) 0.7
Air flow rate, kg/s 30

Ratio
pressure 14.1
bypass 0.78
Dimensions
length, mm 1,915
diameter, mm 621
Engine dry weight, kg 298

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PS-90A Turbofan Engine Technology

PS-90A Turbofan Engine. The PS-90 turbofan engine features a twoshaft configuration with exhaust mixing from both ducts. It has a reverser inside the bypass duct. The engine comprises 11 modules. The
single-stage fan has titanium blades. The lowpressure compressor has two stages, and the high-pressure compressor has 13 stages. The engine has a cannular combustion chamber. The cooled high-pressure turbine has two stages, and the low-pressure turbine has four stages. The engine has a two-channel digital
control system. Advanced control and monitoring system provides timely engine malfunction
detection and on-condition maintenance.

The unified PS-90A engine is designed to power the Tu-204, Tu-214, Tu-330, Il-76MF, Il-76T/TD, and Il-96-300 aircraft. In 1992 the engine got the Interstate Aviation Committee and ICAO noise and emission certificates. Introduction of more stringent ICAO requirements will not pose a problem for PS-90A-powered aircraft as only minor upgrading of the standard engine and air intake noise-absorption
system will be required.

Variants
The PS-90A-76 derivative has an extended service life and improved acoustic and emission characteristics. It is designed to power the Il-76MF aircraft, and can also be installed on the Il-76T/TD and Il-86 aircraft. The PS-90A2 derivative boasts enhanced reliability, improved efficiency, and simplified maintenance.

PS-90A Turbofan Engine Specifications
                                                                       PS-90A                           PS-90A2
Thrust, kgf:
take-off mode (H=0, M=0, ISA)                 16,000                             16,000
cruising mode
(H=11,000 m, V=850 km/h)                        3,500                               3,700
Specific fuel consumption, kg/kgf/h
cruising mode (H=11,000,
V=850 km/h)                                                0.595                                 0.595
Air consumption, kg/sec 470 470
Dimensions, mm:
fan diameter                                                1,900                                  1,900
length 5,333 4,964
Engine dry weight, kg                                2,950                                    2,950

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RD-600V Turboshaft Engine Technologies

RD-600V Turboshaft Engine. The RD-600V turboshaft engine of modular design is installed on the Ka-60/62 multipurpose twin-engine helicopters and its derivatives. The RD-600V is the engine of the new generation of 1,200 to 1,800 hp power class. Its distinguishing features are as follows:

* Reverse-flow combustion chamber

* Two-stage power turbine

* New memory storage

* Automatic electronic digital control system

* Segmented two-wall flame tube that increases the engine overhaul period to 10,000 hours

* Four-stage miniature axial-centrifugal compressor with a controlled starter, featuring a high degree of compression.

The RD-600V engine employs a built-in high-effective dust protector that allows the helicopter to operate at unpaved airfields. The engine intermediate gear box can decelerate the output shaft to 6,000 rpm that considerably simplifies the design of the main rotor drive gear box of the helicopter and provides its best weight characteristics and overall dimensions.

The advanced system of faults monitoring and fully automatic digital two-channel test system of emergency warning greatly improves a factor of safety and reliability of helicopters that make use of this engine. The RD-600V engine is provided with the certificate registered in the Aviation Register of the
Interstate Aviation Committee (АRIAC).


RD-600V Engine Specifications
Power, hp / EM 1,550
Power, hp
takeoff 1,300
cruise 1,000
Specific fuel consumption, g / (hp.h)
takeoff 209
cruise 225
Air flow rate, kg/s 4
Pressure ratio 12.7
Engine dry weight, kg 220
Overhaul period
time between overhauls, hrs 220
service life, hrs 10,000

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TV3-117 and TV7-117 Turboshaft Engine Family

The TV3-117VM/TV3-117VMA turboshaft engine family features a single-shaft configuration. The 12-stage compressor has a variable-area guide vane. The combustion chamber is of a straight-flow annular type. The engine has a twostage free turbine with the overspeeding protection. The exhaust pipe deflects the gas flow by 60 deg. The engine has an electronic-hydromechanical control system.


The engine is designed to power the Mi-8AMT, Mi-8MT, Mi-8MTV, Mi-14, Mi-17, Mi-171, Mi-172, Mi-24, Mi-28, Mi-35, Ka-27, Ka-28, Ka-29, Ka-31, Ka-32, Ka-50, and Ka-52 helicopters. The TV3-117 is one of the world’s most efficient engines in its class. It is easy to operate, maintain and repair. Introduction of the emergency thrust mode allows the helicopter to land safely with one engine failed. A dust guard can be installed.

Operation of the TV3-117 engine for 25 years in 60 countries has proved its exceptional reliability. The TV3-117VM/VMA is certificated by the Aviation Register of the Interstate Aviation Committee and by corresponding bodies of Canada, China, and India.


Turboshaft engine family incorporates the VK-800, VK-1500VM, VK-2500, VK-3000 (TV7-117) and VK-3500 engines. High-end technologies, latest electronic digital systems, soft/hardware and monitoring and diagnostic equipment considerably improve capabilities of helicopters equipped with the new turboshaft engines. These engines differ from the old versions in extended overhaul period of the engine hot components, extra gas-dynamic stability at varying duties, engine parameters accuracy and engine control quality, enhanced monitoring depth providing operation of the engine according to its technical condition and better weight characteristics and overall dimensions.

The VK-800 turboshaft engine of the fifth generation is designed to equip the Mi-54, Ansat and Ka-226 type helicopters. The VK-800V derivative was developed for the power units of helicopters of small and large load-carrying capacity, both in twin- and single-engine configuration. The engine parameters meet the requirements of the tested model of a centrifugal compressor and the single-stage un-cooled turbines. All this simplifies the engine design and reduces expenses for its manufacture and operation. Moreover, the enhanced characteristics of the main units of the engine provide its high efficiency.


The VK-1500VM engine is a turboshaft derivative with the power shaft in a backward position. It was developed for the Mi helicopters fitted with the TV2-117 engines. The VK-2500 turboshaft engine is a highpower derivative of the well-know TV3-117VMA engine. By its fuel efficiency and weight characteristics, the engine holds a firm place among the best world’s models. Modern control system improves the engine performance and provides its high reliability and long service life.


The new VK-3000 (TV7-117V) is based on the certified TV7-117 turboshaft engine. It is unitized
with the base engine by 90 %. The engine has two versions:
 
- with the power shaft in a forward position TV7-117V(VМ) engine for the Mi-38 heli copter and its derivatives
 
- with the power shaft in a backward position TV7-117VK engine for upgrading the Mi-28 and Ka-50/Ka-50-2 helicopters. The VK-3500 engine is designed for the Mi-38 helicopters.

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