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특허 상세정보

Aircraft engine starter integrated boundary bleed system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/00   
미국특허분류(USC) 60/3907 ; 60/39183
출원번호 US-0489150 (1990-03-06)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 26  인용 특허 : 0
초록

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...

대표
청구항

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...

이 특허를 인용한 특허 피인용횟수: 26

  1. Hurwitz, Wayne; Ochs, Stuart S.. Active flow control for nacelle inlet. USP2015109157368.
  2. Coffinberry,George Albert. Air turbine powered accessory. USP2006067059136.
  3. Mackin, Steve G.; Foutch, David W.; Landre, Eric G.. Aircraft bleed air and engine starter systems and related methods. USP20181010100744.
  4. Foutch, David W.; Mackin, Steve G.; Bowman, Michael D.. Bleed air systems for use with aircraft and related methods. USP20180810054051.
  5. Knight, Glenn A; Maguire, Alan R; Robinson, Daniel; Bostock, George; Wilson, Mark J. Compressor tip injector. USP20181210145387.
  6. Glahn, J. Axel; Sahm, Michael K.. Engine integrated auxiliary power unit. USP2005116968701.
  7. Arcas Noe ; Hutto Frederick M. ; Parente Charles A.. Extended reaction acoustic liner for jet engines and the like. USP2000106135238.
  8. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2014098844264.
  9. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2013118572947.
  10. Winter, Michael. Gas turbine engine with pylon mounted accessory drive. USP2017089719428.
  11. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2010087766280.
  12. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2013068459597.
  13. Lui Clarence. Integrated bleed air and engine starting system. USP2001106305156.
  14. Suciu, Gabriel L.; Penda, Allan R.; Merry, Brian D.; Glahn, Jorn A.; Dye, Christoper M.; Snape, Nathan. Integrated thermal management system and environmental control system for a gas turbine engine. USP2015038978351.
  15. Leamy, Kevin Richard; Breig, Benjamin Paul; Epstein, Michael Jay; Parrilla, Javier Armando; Hurt, Matthew John; Brinson, Thomas Edward; Fleming, Andrew James. Jet engine cold air cooling system. USP20190410247100.
  16. Weber, Kent; Kyriazopoulos, Athanasios; Hightower, Peter C.; Burie, Bradley J.. Method and systems for bleed air supply. USP2012098267122.
  17. Weber, Kent; Kyriazopoulos, Athanasios; Hightower, Peter C.; Burie, Bradley J.. Method and systems for bleed air supply. USP2014058733110.
  18. Orlando,Robert Joseph; Moniz,Thomas Ory; Brauer,John C.; Henry,John Leslie; Patt,Raymond Felix; Vondrell,Randy Marinus; Dolan,James Patrick; Krammer,Erich Alois; Kirk,David Cory. Methods and apparatus for assembling gas turbine engines. USP2008047353647.
  19. Ackerman, John Frederick; Wagner, William Kent. Methods and apparatus for operating gas turbine engines. USP2005076920748.
  20. Venkataramani,Kattalaicheri Srinivasan; Butler,Lawrence; Lee,Ching Pang. Methods and apparatus for operating gas turbine engines. USP2006016990797.
  21. Nguyen,Ly D.; Woodcock,Gregory O.; Kujala,Stony. Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine. USP2006087093448.
  22. Atassi, Oliver V.. Nacelle with porous surfaces. USP2015038974177.
  23. Khalid, Syed J.. Positionable ejector member for ejector enhanced boundary layer alleviation. USP2017049630706.
  24. Roberge, Gary D.; Berryann, Andrew P.; Carr, Scott A.. Start system for gas turbine engines. USP20181110125724.
  25. Gupta, Anurag; Graziosi, Paolo; Mani, Ramani. System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine. USP2003126655632.
  26. Wolfe, David; Minh, Nguyen Q.; Meister, Kurt; Matulich, Dan S.. Turbomachine-driven environmental control system. USP2004056735953.