| 摘要 |
A gas turbine engine auxiliary compressor 24, for supplying air for de-icing, or air conditioning 70, in an aircraft is driven from a rotor of the gas turbine engine, via a variable speed drive 36, for operating the auxiliary compressor independently of the aircraft gas turbine engine compressor. Means 21 may be provided for bleeding boundary layer air oil a nacelle 10 or another part of the aircraft outer skin and feeding it to the auxiliary compressor. An air turbine 56 may be provided on a common shaft (58) with the auxiliary compressor and a valve 83 provided to direct an unused portion of the airflow from the auxiliary compressor to the air turbine to help power the auxiliary compressor. Compressed air from a ground supply 82, an on board unit 84, or another engine 88 may be supplied via valve 75 to the air turbine for on ground and in flight starting of the gas turbine engine through the variable speed drive. Alternative arrangements of the auxiliary components and alternative compressor/turbine/drive details are disclosed (figures 1 and 3). <IMAGE>
|
