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MTR MTR390
From Wikipedia, the free encyclopedia
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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]
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Variants
- MTR390-2C
- Production engine
- MTR390-E
- Enhanced variant under development
Applications
Specifications (MTR390)
Data from Aviation Week & Space Technology [2]
General characteristics
- Type: Centrifugal turboshaft
- Length: 108 cm (42.4 in)
- Diameter: 68 cm (26.8 in)
- Dry weight: 169 kg (372 lb)
Components
- Compressor: Centrifugal, 2 stage
- Combustors: Annular
- Turbine: 1 stage high pressure turbine, 2 stage low pressure turbine
Performance
- Maximum power output: 1465 shp (1092kW)
- Overall pressure ratio: 13:1
- Specific fuel consumption: 280 g/kW·h (0.46 lb/shp-hr)
- Power-to-weight ratio: 6.46 kW/kg
See also
Comparable engines
References
External links
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