Rolls-Royce/SNECMA M45H
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| M45H engine on display |
The Rolls-Royce/SNECMA M45H is an Anglo-French medium bypass ratio turbofan produced specifically for the twin-engined VFW-Fokker 614 aircraft in the early 1970s.
The design was started as a collaborative effort between Bristol Siddeley and SNECMA.[1]
Design and development
The VFW 614 was designed to operate over short sectors with up to a dozen flights a day. The engines were optimized for 30-minute sectors at a cruise altitude of 21,000 feet at Mach 0.65. Only a few minutes would be spent at the cruise rating and most of the flight would be at the higher climb rating or at a descent setting. The engine had a low turbine entry temperature and comparatively low rotational speed.[2]
The engine was designed to be uprated without drastic redesign. Three options were water injection (+10% thrust), improved HP turbine (+10% thrust), addition of a zero-stage to the LP compressor (+25% thrust).[2] The M45H-01 was to have a thrust-specific fuel consumption (TSFC) of Script error: No such module "convert"..[3]
The engine was developed at the time of the Rolls-Royce bankruptcy which resulted in delays in developing the engine.[4]
Variants
- M45F
- Civil low bypass turbofan Template:Cvt for take-off.[5]
- M45G
- Military low bypass turbofan Template:Cvt for take-off, wet.[5]
- M45H
- Civil medium bypass turbofan Template:Cvt for take-off, wet.[5]
- RB.410
- Rolls-Royce designation for the M45SD-02 geared turbofan
- M45SD-02
- Template:Cns
Engines on display
Rolls-Royce/SNECMA M45H engines are on display as part of the aero engine collection at the Royal Air Force Museum Cosford and the Musée aéronautique et spatial Safran. Additionally, an engine, with its cowl and pylon, is displayed at the Deutsches Museum Flugwerft Schleissheim; this museum also displays a VFW-614, which has two engines mounted.
Specifications (M45H Mk.501)
Data from Jane's All the World's Aircraft 1971-72.[6]
General characteristics
- Type: Turbofan
- Length: 2,600 mm (102.4in)
- Diameter: 909 mm (35.8 in)
- Dry weight: 673 kg (1,483 lb)
Components
- Compressor: 5-stage intermediate pressure and 7-stage high-pressure axial compressor with a single-stage fan
- Bypass ratio: 2.85:1[7]
- Combustors: Annular with 24 vapourising burners
- Turbine: 3-stage low pressure and single-stage high pressure turbines
- Fuel type: Aviation kerosene (JetA-1 typically)
- Oil system: pressure return system at Template:Cvt
Performance
- Maximum thrust: 7,300 lbf (32.4 kN[8])
- Overall pressure ratio: 16.5:1
- Air mass flow: Template:Cvt
- Thrust-to-weight ratio: 4.9:1
See also
Related development
Comparable engines
Related lists
References
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- ↑ a b Script error: No such module "Citation/CS1".
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- ↑ Swanborough 1971, p.371.
- ↑ a b c Script error: No such module "citation/CS1".
- ↑ J W R Taylor 1971,p.650.
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Further reading
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- Swanborough, Gordon. Air Enthusiast, Volume One. London: Pilot Press, 1971. Template:ISBN.
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External links
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- Stol Fans from Dowty a 1971-01-21 Flight International article
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