MTR MTR390
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), has been developed with Spain's ITP.[1]
Variants
- MTR390-2C
- Production engine
- MTR390-E
- Enhanced variant
Applications
Specifications (MTR390-E)
Data from MTRI,[2]Aviation Week & Space Technology [3]
General characteristics
- Type: Centrifugal turboshaft
- Length: Template:Cvt
- Diameter: 68 cm (26.8 in)
- Dry weight: Template:Cvt
Components
- Compressor: Centrifugal, 2 stage
- Combustors: Annular
- Turbine: 1 stage high pressure turbine, 2 stage low pressure turbine
Performance
- Maximum power output: Template:Cvt at take-off
- Overall pressure ratio: 14:1 at take-off
- Specific fuel consumption: 280 g/kW·h (0.46 lb/shp-hr) (MTR390-C2)
- Power-to-weight ratio: 6.11 kW/kg at take-off
See also
Comparable engines
References
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External links
- Official company page
- MTU MTR390 page
- Rolls-Royce MTR390 page
- Turbomeca MTR390 page
- ITP MTR390-E pageScript error: No such module "Unsubst". (PDF file in English and Spanish)