|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/209 ; 244/1185 ; 244/134R ; 62/DIG ; 5|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 32 인용 특허 : 0|
An aircraft gas turbine engine is provided with an electrically powered boundary layer air bleed apparatus for bleeding boundary layer air off the nacelle and the wing or another part of the aircraft outer skin in order to reduce boundary layer or surface drag and using the boundary layer air as a source of compressed air and cooling air for the aircraft\s environmental control system (ECS).
An apparatus for bleeding boundary layer air from a portion of the outer surfaces of a gas turbine engine powered aircraft, wherein said apparatus comprises: an electrically powered bleed air compressor means in fluid supply communication with the aircraft\s outer surface and effective for bleeding boundary layer air from the aircraft\s outer surface and powered by an aircraft gas turbine engine powered electrical generator, said bleed air compressor means comprising an electrically powered nacelle compressor means in fluid supply communication with a po...