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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.
Design and development
The single-stage fan, together with a five-stage LP compressor, was driven by a three-stage LP turbine, whilst the seven-stage HP compressor was driven by a single-stage, air-cooled, HP turbine. An annular combustor and an unmixed exhaust, with a plug-type primary nozzle, were other design features.
The engine was developed at the time of the Rolls-Royce bankruptcy which resulted in delays in developing the engine.
was a derivative of the M45H-01 turbofan, designed 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... Read More