|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/209 ; 244/1185 ; 244/53R ; 454/71|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 77 인용 특허 : 0|
An aircraft gas turbine engine is provided with a starting air turbine that is directly connected through the starter gearbox to the high pressure (HP) shaft and is provided with an apparatus to extract excess energy from engine compressor bleed air, return it to the engine, and to start the engine with compressed air from starting air sources, and to cool and provide compressed air for powering the Environmental Control System (ECS) and using the bleed air for cabin refreshening. The air turbine may be connected to a nacelle boundary layer bleed compres...
An environmental control system and aircraft boundary layer bleed system apparatus powered by an aircraft propulsive gas turbine engine, said apparatus comprising: a bleed air means to bleed compressor bleed air from a compressor stage of the gas turbine engine, a starting air turbine in fluid supply communication with said bleed air means effective for extracting energy from the bleed air supplied by said bleed air means and converting the extracted energy to useful work, a work transmission means operably connected to said starting air turbine effectiv...