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특허 상세정보

MyON담기
내보내기 페이스북 공유 카카오톡 공유

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

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/209 ; 244/1185 ; 244/53R ; 454/71
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 compres...

대표
청구항
▼

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...

이 특허를 인용한 특허 (77)

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  8. Mackin, Steve G.; Foutch, David W.; Landre, Eric G., Aircraft bleed air and engine starter systems and related methods.
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  10. Stretton,Richard G, Aircraft engine arrangement.
  11. Meister, Jürgen, Aircraft with a fluid-duct-system.
  12. Rolling, August J; Heiser, William H; Wisniewski, Charles F, Augmented propulsion system with boundary layer suction and wake blowing.
  13. Glahn, Jorn A., Bearing compartment pressurization and shaft ventilation system.
  14. Lo, Charles, Bi-metallic actuator for selectively controlling air flow between plena in a gas turbine engine.
  15. Foutch, David W.; Mackin, Steve G., Bleed air systems for use with aircraft and related methods.
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  21. Fucke, Lars; Daggett, David L., Combined fuel cell aircraft auxiliary power unit and environmental control system.
  22. Fucke,Lars; Daggett,David L., Combined fuel cell aircraft auxiliary power unit and environmental control system.
  23. Moravec,Bradford L.; Boggs,Royal E.; Graham,Rodney N.; Grim,Alan; Adkins,David A.; Snow, Jr.,Donald; Haack,Greg A., Commercial aircraft on-board inerting system.
  24. Knight, Glenn A; Maguire, Alan R; Robinson, Daniel; Bostock, George; Wilson, Mark J, Compressor tip injector.
  25. Liu, Xiaoliu, Cooler in nacelle with radial coolant.
  26. Westenberger, Andreas; Arendt, Martin; Marquardt, Till; Frahm, Lars; Schrauf, Geza, Cooling system on the basis of suction of a boundary layer.
  27. Caruel, Pierre; Hurlin, Hervé, De-icing and conditioning device for an aircraft.
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  29. Metzger, III, Edward H., Dual pass air conditioning unit.
  30. Violett, Robert S., Electric propulsion system useful in jet-type model airplanes and UAVS.
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  38. Morford, Stephen A.; Larkin, Michael J., Gas turbine engine having slim-line nacelle.
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  41. Winter, Michael; Jain, Ashok K., Gas turbine engine system providing simulated boundary layer thickness increase.
  42. Winter, Michael, Gas turbine engine with pylon mounted accessory drive.
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  75. Jain, Ashok K.; Winter, Michael, Variable contraction ratio nacelle assembly for a gas turbine engine.
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