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.

MTR390
Type	Turboshaft
Manufacturer	MTU Turbomeca Rolls-Royce
First run	December 1989
Major applications	Eurocopter Tiger

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

• Eurocopter Tiger

Specifications (MTR390)

Data from [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

• Avco/Pratt & Whitney T800
• HAL HTSE-1200
• Safran Ardiden

References

External links

Wikimedia Commons has media related to MTR390.

• Official company page
• MTU MTR390 page
• Rolls-Royce MTR390 page
• Turbomeca MTR390 page
• ITP MTR390-E page^{[permanent dead link]} (PDF file in English and Spanish)

На других языках

[de] MTR390

[es] MTR MTR390

[fr] MTR MTR390