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 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 12.91 grams per kilonewton per second (0.456 pounds per pound-force per hour).[3]
The engine was developed at the time of the Rolls-Royce bankruptcy which resulted in delays in developing the engine.[4]
Variants
The M45SD-02 variable geometry fan engine at the New Mills Technology Centre.
M45F
Civil low bypass turbofan 7,915 lbf (35.21 kN) for take-off.[5]
M45G
Military low bypass turbofan 13,200 lbf (58.72 kN) for take-off, wet.[5]
M45H
Civil medium bypass turbofan 7,880 lbf (35.05 kN) for take-off, wet.[5]
RB.410
Rolls-Royce designation for the M45SD-02 geared turbofan
M45SD-02
A derivative of the M45H-01 turbofan, designed[when?] to demonstrate ultra-quiet engine technologies, needed for STOL aircraft operating from city centre airports. A geared, variable pitch fan, replaced the first stage of the low pressure (LP) compressor. A modest fan pressure ratio, consistent with the high bypass ratio, meant a low fan tip speed could be employed. A low hot jet velocity was another major design feature. In reverse thrust, intake air entered the bypass duct, via a gap in the cold nozzle outer wall, and went through the fan, to be expelled through the intake. A small proportion of the bypass duct air entered the IP compressor, via a special diverter valve, to sustain the gas generator. Reverse thrust was obtained by the fan going through fine (rather than feather) pitch. Engine testing took place in the mid 1970s. The chief engineer of this project was David McMurtry, co-founder and Chairman of Renishaw PLC. After the prototype engine was stored,[when?] it was given to McMurtry for safe keeping at the New Mills site.[citation needed]
^. Flight International. 6 January 1966. p. 28. Archived from the original on 10 November 2013.
^ ab. Flight International. 18 April 1974. pp. 485–488. Archived from the original on 4 March 2016. Includes . {{cite magazine}}: External link in |postscript= (help)CS1 maint: postscript (link)
^Bose, T. (2012). Airbreathing propulsion: An introduction(PDF). Springer Aerospace Technology. Springer Science+Business Media, LLC. p. 288. doi:10.1007/978-1-4614-3532-7. ISBN978-1-4614-3531-0.
^(PDF). Flight International. 4 November 1971. p. 730. Archived from the original (PDF) on 6 March 2016.
^(PDF). Archived from the original (PDF) on 6 June 2011. Retrieved 21 October 2007.{{cite web}}: CS1 maint: archived copy as title (link)
Further reading
Davies, D. G. M.; Miller, D. C. (19–20 May 1976). A variable pitch fan for an ultra quiet demonstrator engine. 1976 Spring Convention: Seeds for Success in Civil Aircraft Design in the Next Two Decades. Royal Aeronautical Society. pp. 1–18.
Stevens, James Hay (12 August 1971). "Rolls-Royce design for quieter airliners". New Scientist and Science Journal. Vol. 51, no. 764. pp. 376–377. ISSN 0369-5808.
Swanborough, Gordon. Air Enthusiast, Volume One. London: Pilot Press, 1971. ISBN0-385-08171-5.
Wright, G. H.; Russell, J. G. (18 March 1980). "The M.45SD-02 variable pitch geared fan engine demonstrator test and evaluation experience". The Aeronautical Journal of the Royal Aeronautical Society (published September 1980). 84 (836): 268–277. ISSN 0001-9240. OCLC 8272365305.
External links
Wikimedia Commons has media related to Rolls-Royce/SNECMA M45H.
a 1971-01-21 Flight International article
January 07, 2023
rolls, royce, snecma, m45h, anglo, french, medium, bypass, ratio, turbofan, produced, specifically, twin, engined, fokker, aircraft, early, 1970s, m45hm45h, engine, displaytype, turbofannational, origin, united, kingdom, francemanufacturer, rolls, royce, snecm. 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 M45HM45H engine on displayType TurbofanNational origin United Kingdom FranceManufacturer Rolls Royce SNECMAFirst run 1970Major applications VFW Fokker 614Developed from SNECMA M45The design was started as a collaborative effort between Bristol Siddeley and SNECMA 1 Contents 1 Design and development 2 Variants 3 Engines on display 4 Specifications M45H Mk 501 4 1 General characteristics 4 2 Components 4 3 Performance 5 See also 6 References 7 Further reading 8 External linksDesign and development Edit An M45H in its overwing mount on the VFW Fokker 614 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 12 91 grams per kilonewton per second 0 456 pounds per pound force per hour 3 The engine was developed at the time of the Rolls Royce bankruptcy which resulted in delays in developing the engine 4 Variants Edit The M45SD 02 variable geometry fan engine at the New Mills Technology Centre M45F Civil low bypass turbofan 7 915 lbf 35 21 kN for take off 5 M45G Military low bypass turbofan 13 200 lbf 58 72 kN for take off wet 5 M45H Civil medium bypass turbofan 7 880 lbf 35 05 kN for take off wet 5 RB 410 Rolls Royce designation for the M45SD 02 geared turbofan M45SD 02 A derivative of the M45H 01 turbofan designed when to demonstrate ultra quiet engine technologies needed for STOL aircraft operating from city centre airports A geared variable pitch fan replaced the first stage of the low pressure LP compressor A modest fan pressure ratio consistent with the high bypass ratio meant a low fan tip speed could be employed A low hot jet velocity was another major design feature In reverse thrust intake air entered the bypass duct via a gap in the cold nozzle outer wall and went through the fan to be expelled through the intake A small proportion of the bypass duct air entered the IP compressor via a special diverter valve to sustain the gas generator Reverse thrust was obtained by the fan going through fine rather than feather pitch Engine testing took place in the mid 1970s The chief engineer of this project was David McMurtry co founder and Chairman of Renishaw PLC After the prototype engine was stored when it was given to McMurtry for safe keeping at the New Mills site citation needed Engines on display Edit Cutout at the Aeronauticum museum Rolls Royce SNECMA M45H engines are on display as part of the aero engine collection at the Royal Air Force Museum Cosford and the Musee aeronautique 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 EditData 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 207 kPa 30 psi Performance Maximum thrust 7 300 lbf 32 4 kN 8 Overall pressure ratio 16 5 1 Air mass flow 104 kg s 13 757 lb min Thrust to weight ratio 4 9 1See also EditRelated development SNECMA M45Comparable engines General Electric CF34Related lists List of aircraft enginesReferences Edit Bristol Siddeley engines Flight International 6 January 1966 p 28 Archived from the original on 10 November 2013 a b M45H Power for VFW Fokker 614 Flight International 18 April 1974 pp 485 488 Archived from the original on 4 March 2016 Includes engine cutaway a href Template Cite magazine html title Template Cite magazine cite magazine a External link in code class cs1 code postscript code help CS1 maint postscript link Bose T 2012 Airbreathing propulsion An introduction PDF Springer Aerospace Technology Springer Science Business Media LLC p 288 doi 10 1007 978 1 4614 3532 7 ISBN 978 1 4614 3531 0 Swanborough 1971 p 371 a b c Wilkinson Paul H 1966 Aircraft engines of the World 1966 77 21st ed London Sir Isaac Pitman amp Sons Ltd pp 165 167 J W R Taylor 1971 p 650 614 VFW s jet feederliner PDF Flight International 4 November 1971 p 730 Archived from the original PDF on 6 March 2016 Archived copy PDF Archived from the original PDF on 6 June 2011 Retrieved 21 October 2007 a href Template Cite web html title Template Cite web cite web a CS1 maint archived copy as title link Further reading EditDavies D G M Miller D C 19 20 May 1976 A variable pitch fan for an ultra quiet demonstrator engine 1976 Spring Convention Seeds for Success in Civil Aircraft Design in the Next Two Decades Royal Aeronautical Society pp 1 18 Stevens James Hay 12 August 1971 Rolls Royce design for quieter airliners New Scientist and Science Journal Vol 51 no 764 pp 376 377 ISSN 0369 5808 Swanborough Gordon Air Enthusiast Volume One London Pilot Press 1971 ISBN 0 385 08171 5 Wright G H Russell J G 18 March 1980 The M 45SD 02 variable pitch geared fan engine demonstrator test and evaluation experience The Aeronautical Journal of the Royal Aeronautical Society published September 1980 84 836 268 277 ISSN 0001 9240 OCLC 8272365305 External links Edit Wikimedia Commons has media related to Rolls Royce SNECMA M45H Stol Fans from Dowty a 1971 01 21 Flight International article Retrieved from https en wikipedia org w index php title Rolls Royce SNECMA M45H amp oldid 1131406887, wikipedia, wiki, book, books, library,
