In a gas turbine engine, the booster compressor is driven by both the low pressure or fan shaft and high pressure shaft through a differential gear arrangement. The rotational speed of the booster compressor is intermediate between the speed of the fan and the speed of the high pressure compressor.
申请公布号
WO2014177836(A1)
申请公布日期
2014.11.06
申请号
WO2014GB51024
申请日期
2014.04.01
申请人
DERWENT AVIATION CONSULTING LTD;SPEAK, TREVOR H.;SELLICK, ROBERT J.
