| 词条 | Rolls-Royce/SNECMA M45H | ||||||||||||||
| 释义 |
The Rolls-Royce/SNECMA M45H was a 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 developmentThe 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 engine was developed at the time of the Rolls-Royce bankruptcy which resulted in delays in developing the engine.[3] Variants
Engines on displayA Rolls-Royce/SNECMA M45H engine is on display as part of the aero engine collection at the Royal Air Force Museum Cosford. Specifications (M45H Mk.501){{jetspecs||ref=Jane's All the World's Aircraft 1971-72.[5] |type=Turbofan |length=2,600 mm (102.4in) |diameter=909 mm (35.8 in) |weight=673 kg (1,483 lb) |compressor=5-stage intermediate pressure and 7-stage high-pressure axial compressor with a single-stage fan
|combustion=Annular |turbine=3-stage low pressure and single-stage high pressure turbines |fueltype= |oilsystem= |power= |thrust=7,300 lbf (32.4 kN[7]) |compression=16.5:1 |aircon= |turbinetemp= |fuelcon= |specfuelcon= |power/weight= |thrust/weight=4.9:1 }} Specifications (M45SD-02){{jetspecs||ref=Flight International 1973 [8] |type=turbofan |length= |diameter= |weight= |compressor=5-stage intermediate pressure and 7-stage high-pressure axial compressor with a geared, single-stage, variable-pitch, fan |bypass=8.73:1 |combustion=Annular |turbine=4-stage low pressure and single-stage high pressure turbines |fueltype= |oilsystem= |power= |thrust=10,000 lbf (44.48 kN) |compression<16.5:1 |aircon= |turbinetemp= |fuelcon=3 200 lb/hr (1,451 kg/hr) |specfuelcon=0.32 lb/hr/lbf (9.064 g/s/KN) |power/weight= |thrust/weight= }} See also{{aircontent|see also= |related= |similar aircraft= |lists=
|similar engines=
}} References
1. ^Flight 6 January 1966 2. ^1 https://www.flightglobal.com/pdfarchive/view/1974/1974%20-%200622.html 3. ^Swanborough 1971, p.371. 4. ^1 2 {{cite book |last=Wilkinson |first=Paul H. |title=Aircraft engines of the World 1966/77 |year=1966 |publisher=Sir Isaac Pitman & Sons Ltd. |location=London |edition=21st|pages=165-167}} 5. ^J W R Taylor 1971,p.650. 6. ^http://www.flightglobal.com/FlightPDFArchive/1971/1971%20-%202336.PDF 7. ^{{cite web |url=http://www.caa.co.uk/docs/702/1RR001_01102004.pdf |title=Archived copy |accessdate=2007-10-21 |deadurl=yes |archiveurl=https://web.archive.org/web/20110606141727/http://www.caa.co.uk/docs/702/1RR001_01102004.pdf |archivedate=6 June 2011 |df=dmy-all }} 8. ^{{citation |url=http://www.flightglobal.com/FlightPDFArchive/1973/1973%20-%201027.PDF |format=pdf |journal=Flight International |date=19 April 1973 |page=615 |title=Progress in Britain |last=D. G. M. Davis}}
External links{{Commons category}}
3 : Medium-bypass turbofan engines|Turbofan engines 1970–1979|Rolls-Royce aircraft gas turbine engines |
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