|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3907 ; 60/39183|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 26 인용 특허 : 0|
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 nacel...
An apparatus for supplying an aircraft with auxiliary compressed air and integral with an aircraft propulsive gas turbine engine having a rotor, said apparatus comprising: an auxiliary compressor for supplying the auxiliary compressed air, a means for mechanically driving said auxiliary compressor from the rotor of the gas turbine engine, a cycle varying means for operating the cycle of said auxiliary compressor independently from the cycle of the aircraft gas turbine engine, an air turbine on a common shaft with said auxiliary compressor, a means capabl...