M45SD-02

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The M45SD-02 was a derivative of the Rolls-Royce/SNECMA 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 -01 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 1970's.

Static Thrust: 9-10000lbf Bypass Ratio: 10 (approximately)