F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
60/183
F02C 7/057 (2006.01) F02C 6/08 (2006.01) F02C 7/32 (2006.01) F02C 7/36 (2006.01) F04D 25/02 (2006.01)
Patent
CA 2036822
13DV-9963 ABSTRACT An aircraft gas turbine engine is provided with a compressed air supply system generally used for meeting customer or aircraft bleed air requirements. The compressed air supply system comprises an auxiliary compressor, a means for mechanically driving the system from a rotor of the gas turbine rotor, and a cycle varying means, such as a variable speed drive, for operating the auxiliary compressor cycle independently of the aircraft gas turbine engine compressor cycle. The preferred embodiment provides a means for bleeding boundary layer air off the nacelle or another part of the aircraft outer skin and using it as a source of air for the auxiliary compressor. one embodiment includes an air turbine on a common shaft with the auxiliary compressor and a means to direct an unused portion of the airflow form the auxiliary compressor to the air turbine to help power the auxiliary compressor and another embodiment includes a means to direct compressed starting air to the air turbine for on ground and in flight starting of the gas turbine engine through the variable speed drive and a mechanical linkage to the high rotor of the gas turbine engine.
Company General Electric
Craig Wilson And Company
Davison Samuel H.
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