MTR MTR390
From Wikipedia, the free encyclopedia
The MTU Turbomeca Rolls-Royce MTR390 is a turboshaft developed for light helicopter applications by MTU Turbomeca Rolls-Royce (MTR). The engine is designed to power helicopters in the weight range of 5-7 tonnes in both single and twin engine configurations. So far the only application is the Eurocopter Tiger. Test runs of the MTR390 began in 1989 and the first test flight was performed in 1991. The MTR390 received military certification in May 1996 and civil approval in June 1997.
An uprated version, the MTR390-E (Enhanced), is being developed with Spain's ITP.[1]
Variants
- MTR390-2C
- Production engine
- MTR390-E
- Enhanced variant under development
Applications
Specifications (MTR390)
Data from [2]
General characteristics
- Type: Centrifugal Turboshaft
- Length: 42.4 in (108 cm)
- Diameter: 26.8 in (68 cm)
- Dry weight: 372 lb (169 kg)
Components
- Compressor: Centrifugal, 2 stage
- Combustors: Annular
- Turbine: 1 stage high pressure turbine, 2 stage low pressure turbine
Performance
- Maximum power output: 1465 shp
- Overall pressure ratio: 13:1
- Specific fuel consumption: 0.46 lb/shp-hr
- Power-to-weight ratio:
References
- ↑ http://www.mtr390.com/_mtri/index.php?rubric=mtri_technical_information
- ↑ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 121.
External links
- Official company page
- MTU MTR390 page
- Rolls-Royce MTR390 page
- Turbomeca MTR390 page
- ITP MTR390-E page (PDF file in English and Spanish)
| |||||||||||||||||
| ||||||||||||||
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.