[특허]Gas turbine engine powered aircraft environmental control system and boundary layer bleed

Gas turbine engine powered aircraft environmental control system and boundary layer bleed 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-021/06
출원번호	US-0738985 (1991-08-01)
발명자 / 주소	Coffinberry George A. (West Chester OH)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 77 인용 특허 : 0

초록 ▼

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 compressor to bleed boundary layer air from a forward portion of the nacelle to reduce nacelle surface drag. The ECS may be provided with a wing boundary layer bleed means which uses a cooling air fan in the ECS to draw cooling air through the heat exchangers in the ECS pack from the boundary layer air from a forward portion of the aircraft\s wing to reduce its surface drag.

대표청구항 ▼

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 effective to return the work from said air turbine to the engine, a first bleed duct in fluid supply communication with said energy extraction and work conversion means to supply bleed air exhaust from said air turbine to a means for conditioning cabin air for an aircraft, and at least one means for bleeding boundary layer air form the surface of the aircraft.

이 특허를 인용한 특허 (77)

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Jain, Ashok K.; Chaudhry, Zaffir A., Variable shape inlet section for a nacelle assembly of a gas turbine engine.
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Gas turbine engine powered aircraft environmental control system and boundary layer bleed 원문보기

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Gas turbine engine powered aircraft environmental control system and boundary layer bleed 원문보기

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