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Aviation engines ÒV2-117À and ÒV2-117 are designed to be operated in helicopters ÌI-8. Technical characteristics and performance of ÒV2-117À and ÒV2-117 engines correspond to up-to-date technical requirements, applied to this class of engines.
Engine’s singularity is the presence of free turbine in them (screw turbine) for engine power transfer to gearbox VR-8.
Free turbine cinematically is not connected with turbocompressor part of engine. Propulsion system of a helicopter includes two engines and VR-8. In case of need, one engine’s power is enough for flight continuation. Right and left engines are interchangeable on condition of exhaust manifold turn. A helicopter can operate on engines TV2-117 and ÒV2-117 À . In order to replace one engine by another no extra work is required. Joint operation of engines ÒV2-117 è ÒV2-117À is permitted on one helicopter. Engines on a helicopter are jointed to one main gearbox VR-8, which transfer power form engines to main rotor and tail rotor. The propulsion system of a helicopter has the system of automatic control for main rotor’s turns and synchronization of power of both engines. Every engine has separate systems: of lubrication, of fueling, of regulation, of anti-icing, and can operate on a helicopter without assistance of the second engine.
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Designation |
ÒV2-117À (ÒV2-117) |
Type of engine |
Gas-turbine, with free turbine |
Direction of rotation of compressor rotors, compressor turbine and free turbine (if look in flight direction) |
left |
Dry weight of engine, kg |
No more than 330 + 2% |
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Length with units and an exhaust manifold |
2835 |
The length from a helicopter air inlet joint flange up to a gearbox joint flange |
2391 |
Width |
547 |
Height |
747 |
| Compressor |
axial , 10-stage |
| Combustion chamber |
Annular, with 8 heads for nozzles |
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Of compressor |
axial, 2-stage |
free |
axial, 2-stage |
Exhaust system |
Not regulating system, exhaust through a socket, under angle of 60 degrees to an axis of an engine |
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For a helicopter ÌI -8
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A Turbine shaft engine ÒÂ3-117 is designed to be operated in helicopters. It is one of the best engines in the world if take into account efficiency in its class of engines, achieved due to high efficiency output of main assembly units (compressor efficiency is equal to 86%, compressor turbine efficiency - 91%, free turbine efficiency - 96%). Values of specific fuel rate and specific weight are in correspondence with best international standards.
Engine has great gas-dynamic stability margins. In engine’s design new advanced technologies were applied:
titanium compressor rotor, bonded out of separate discs by means of electron-beam welding;
titanium-alloy compressor blades and vanes, produced by methods of cool expander;
contact graphite seals in oil chambers;
the electronic- hydromechanical control system is used for latest up-to-date versions and so on.
The engine has long life, high reliability, good serviceability and reparability.
Another application of Engine ÒV3-117: in addition to helicopters, it can be used in different water-crafts, as a drive of generators and compressors of oil-gas-transfer stations. In jet variant (without free turbine module) the engine can be applied for the purpose of exhaust jet drying of livestock’s houses, buildings under construction, blowing off snow and ice from main roads, railroads, airfields.
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| Engine’s versions / Parameter |
Ò V3-117V
1981 |
ÒV3-117VÊ
1985 |
ÒV3-117VÌ
1987 |
ÒV3-117ÂÌÀ
1987 |
ÒÂ3-117VÌ-02
1993 |
ÒV3-117VÌÀ-02
1993 |
ÒV3-117ÌÒ
1977 |
| Power, h.p.:
emergency rate
takeoff rate
cruise |
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2100
1500 |
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2200
1500 |
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2000
1500 |
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2200
1500 |
2200
2000
1500 |
2400
2200
1500 |
2200
2000
1500 |
| Specific consumption, g/h.p. hour: takeoff rate |
210+5% |
230
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| Degree of air pressure increase in compressor: - takeoff rate |
9.40
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| Max gas temperature Ìàõ ahead of turbine, C:
- takeoff rate |
1263 |
| Life time, hour:
specified
overhaul |
6000
1500
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| Dimensions, mm:
length
height
width |
2055
728
660 |
| Weight, kg |
285 |
293 |
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Main helicopter’s types, where engine TV3-117 are installed |
Engines |
Type of a helicopter |
ÒV3-117VÌ |
ÌI-8ÌÒV/ÀÌÒ/ÌÒ, ÌI-14, ÌI-17, ÌI-171, ÌI-172 |
ÒV3-117VÌÀ |
Êà-29, Êà-32, Êà-50, Êà-52, ÌI-28, Êà-27, Êà-32Ò,
Êà-32À, Êà-32Ñ, ÌI-24, ÌI-24 D |
ÒV3-117VÌ, 02 series |
ÌI-8ÌÒV/ÀÌÒ |
ÒV3-117VÌÀ, 02 series |
Êà-32À, Êà32 |
ÒV3-117ÌÒ |
ÌI-8ÌÒ, ÌI-17 |
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For helicopters: ÌI-8ÌÒ (ÌI-17), ÌI-14
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For helicopters: ÌI-8ÌÒV, ÌI-17
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| Power, kilowatt |
18000 |
| Effective efficiency,% |
31 |
| Weight of an engine together with a platform with a frame, kg |
7800 |
| Dimensions of an engine, ìì |
6200õ2160õ2180 |
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| Mainline jet aircrafts ÒU-154 and ÒU-154 À are operated on engines NÊ-8-2 and NÊ-8-2U. The main distinction features of ÒU-154 À from its predecessor is replacement of an engine NÊ-8-2 with takeoff thrust of 9500 kgf by an engine NÊ-8-2U with larger takeoff thrust. Turbofan engine NÊ -8-2U represents a two-circuit, two-stage, gas-turbine engine with mixture of flows of air and gas. This engine is a version of an engine NÊ-8-2, it has high thrust, reduced fuel rate, and increased rod of reversing gear. At takeoff and cruise rates an engine NÊ-8-2U has high gas-dynamic stability margin. An engine NÊ-8-2U is installed with warning system of critical temperature of bearings ÑÒÏ -3 and limitation system of temperature of outlet gases ÐÒ -12-9 ÀÒ. In oil system, in line of oil evacuation from supports there are magnetic plugs, due to which state of rotor supports can be defined. Works, aimed to increase reliability of assembly units and their life time, are applied for engines. Two external engine – the first and the third – are installed into easy-off gondolas on horizontal pylons, and the second engine is installed into internal gondolas inside fuselage. In order to improve landing characteristics of an aircraft, external engines are installed with reverse rods. For the purpose of serviceability all units are situated in low part of an engine. Length and quantity of turbopipes are maximally reduced.
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| Type of an engine |
turbofan , two-circuit |
| by-pass ratio of an engine |
1 |
| Total compression ratio of a compressor at takeoff rate (under H=0; V=0; MCA) |
10,8 |
| Thrust at takeoff rate (under H=0; V=0; MCA) |
105000 kgf |
| Negative draft at a rate not higher than nominal rate ( ïðè H=0; V=0; MCA) |
3600 ± 150 kgf |
| Acceleration time till a rate of 95% maximum rod of reversing gear |
6 sec |
| Acceleration time of an engine |
8 - 10 ñ sec |
| Length of an engine with reversing gear and nozzle |
5288 mm
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| Length of an engine with jet nozzle |
4762 mm |
| Maximum diameter of an engine |
1442 mm |
| Dry weight of an engine |
2100 kg ± 2%
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| Dry weight of an engine with reversing gear and nozzle |
2350 kg ± 2%
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| Engine’s life time |
Specified by bulletins |
| Shelf life (storage period) of a preserved engine |
5 years |
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An Engine GTD-350 was designed in the early sixties for a lightweight multipurpose helicopter ÌI-2 and was put into full-scale production by the polish enterprise “WSK-Rzeszow ”, where it is produced until now. On the basis of this engine some prototype aviation and transport versions were made: for aircrafts À n-14 Ì and Be-30, helicopters MI-20, racing cars (Gorkovskij motor-car factory), hydrofoil boats (Leningradskij SRI of shipbuilding industry), driving railway vehicle (Scientific and research institute (SRI) of rail transport) and so on.
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Power of power turbine, hp |
350 |
Engine’s mass , kg |
135 |
Turns of power turbine, rpm |
5900 |
Turns of turbocompressor , rpm |
45000 |
Turns of turbocompressor (idling), rpm |
27000 |
Fuel |
kerosene |
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This engine is operated on the ground and in flight, and designed for air supply into helicopter engine starting system and for supply of electrical energy into airborne network of a helicopter while checking electro and radio equipment.
If necessary it can be used as a standby power source.
This engine was constructed as a separate structurally completed unit with its own fuel system, autonomous oil system, regulating system.
Simplicity of design provides its reliability in operation. This engine is a mandatory component of the propulsion system of helicopters ÌI-8ÌÒV-1, ÌI-14, ÌI-17, ÌI-24, ÌI-28, Êà-27, Êà-28, Êà-32, Êà-50. |
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Nominal speed, min -1 |
36750 +-475 |
Quantity of takeoff air, êg/sec |
0,4 |
Total pressure of takeoff air, Mega Pascal |
No less than 0,29
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Temperature of takeoff air, K |
433 |
Fuel flow, kg/h
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No less than 80 |
Gas temperature outside turbine, Ê
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1023 |
Dimensions, mm |
888õ530õ490 |
Dry weight, kg
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70 |
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