Klimov TV2-117
From Wikipedia, the free encyclopedia
| Type | Turboshaft |
|---|---|
| Manufacturer | Klimov |
| First run | 1962 |
| Major applications | Mil Mi-8. |
| Number built | 23,000 |
| Developed from | Klimov TV3-117 |
The Klimov TV2-117 (initially Isotov TV2-117) is a Soviet gas-turbine turboshaft engine intended for helicopter use. Designed in the early 1960s by the Isotov Design Bureau the engine became the first purpose built gas turbine engine for helicopter use by the Soviet Union with previous helicopter turbines being adapted aeroplane powerplants. It was later produced by Klimov, production ending in 1997.[1]
The TV2-117 is claimed to be the most popular helicopter powerplant worldwide and has accumulated over 100 million hours in service. [1]
Variants
Source:Klimov.[1]
- TV2-117
- Base variant.
- TV2-117A
- Improved engine with more durable compressor stator blades.
- TV2-117AG
- Carbon sealed shaft bearings
- TV2-117F
- Limited production of engine certified to FAA airworthiness standards for Japan.
- TV2-117TG
- Multi-fuel variant, adapted to run on liquid petroleum gas and other fuels, such as gasoline an diesel fuel, and for use in cold climates.
Applications
- Antonov An-24 (intended coupled turboprop application)
- Mil Mi-8
- Mil Mi-14
Specifications (TV-2 117)
Data from Gunston.[2]
General characteristics
- Type: Turboshaft
- Length: 2,835 mm (9.301 ft)
- Diameter:
- Dry weight: 330 kg (728 lb) (minus accessories)
Components
- Compressor: Ten-stage axial flow
- Combustors: Eight-chamber cannular
- Turbine: Two-stage compressor turbine, two-stage power turbine
Performance
- Maximum power output: 1,700 hp (1,268 kW)
- Overall pressure ratio: 6.6:1 at 21,200 rpm
- Specific fuel consumption: 0.606 lb/hr/shp
- Power-to-weight ratio:
See also
- Comparable engines
- Related lists
References
 |
Wikimedia Commons has media related to Isotov TV2-117. |
- Notes
- ↑ 1.0 1.1 1.2 Klimov TV2-117 product page Retrieved: 24 May 2012
- ↑ Gunston 1989, p. 81.
- Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
| ||||||||||||||
| ||||||||||||||
This article is issued from Wikipedia. The text is available under the Creative Commons Attribution/Share Alike; additional terms may apply for the media files.