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특허 상세정보

Gas turbine engine with recirculating bleed

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-003/00   
미국특허분류(USC) 60/39.52 ; 60/226.1
출원번호 US-0695513 (1976-06-14)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Lawrence, Derek P.Lampe, Jr., Robert C.Manning, John R.
인용정보 피인용 횟수 : 26  인용 특허 : 0
초록

A method of reducing carbon monoxide and unburned hydrocarbon emissions in a gas turbine engine by bleeding hot air from the engine cycle and introducing it back into the engine upstream of the bleed location and upstream of the combustor inlet. As this hot inlet air is recycled, the combustor inlet temperature rises rapidly at a constant engine thrust level. In most combustors, this will reduce carbon monoxide and unburned hydrocarbon emissions significantly. The preferred locations for hot air extraction are at the compressor discharge or from within t...

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이 특허를 인용한 특허 피인용횟수: 26

  1. Mons, Claude Marcel. Actuating device, bypass air bleed system equipped therewith, and turbojet engine comprising these. USP2013058448446.
  2. Porte, Alain. Aircraft propulsion assembly comprising hot air bleed systems. USP2014038677764.
  3. Laster,Walter Ray; Bandaru,Ramarao V.; Baer,Joan Mae. Control of gas turbine for catalyst activation. USP2006087096667.
  4. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  9. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  10. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  11. Clemen, Carsten; Sielaff, Enrique. Jet engine with compressor air circulation and method for operating the jet engine. USP2014048683811.
  12. Baer,Joan Mae; Laster,Walter Ray; Keller,Douglas Allen. Method for operating a gas turbine. USP2006107124591.
  13. Frutschi Hansulrich (Riniken CHX). Method for regulating a power plant containing a gas turbine assembly and apparatus for the performance of the aforesaid. USP1979084163365.
  14. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  15. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  16. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  17. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  18. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  19. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  20. Nenmeni, Vijay Anand Raghavendran; Alexander, Michael Joseph; Plummer, Paul William; Janssen, Timothy Lee. System and method for air extraction from gas turbine engines. USP20180810041407.
  21. Leachman,David Paul; Sailer,Edward David; Bloomberg,John Eric. System and method for improving thermal efficiency of dry low emissions combustor assemblies. USP2007037185495.
  22. Ress, Jr., Robert A.. Three spool gas turbine engine having a clutch and compressor bypass. USP2014118887485.
  23. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  24. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  25. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  26. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.