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특허 상세정보

Air blast fuel injecton system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F23R-003/32    F02C-007/22   
미국특허분류(USC) 60/3936 ; 60/737 ; 60/738 ; 60/743
출원번호 US-0966903 (1992-10-23)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 14  인용 특허 : 0
초록

In order to enhance fuel injection efficiency, and particularly to atomize low fuel flows at high velocity with low fuel pressure, a fuel injection system 24 for a combustor 22 of a turbine engine 20 has an air blast tube 48 and a fuel supply tube 76. The air blast tube 48 is mounted at an acute angle relative to a wall 26 of the combustor 22 and has a first end 50 in communication with the combustor 22 and a second, enlarged end 52 disposed at an acute angle to an axis 54 of the air blast tube 48 in communication with a source of compressed air external...

대표
청구항

A fuel injection system for a combustor of a turbine engine, comprising: an air blast tube mounted at an acute angle relative to a wall of said combustor, said air blast tube having a first end in communication with said combustor and a second, enlarged end disposed at an acute angle to an axis of said air blast tube and in communication with a source of compressed air externally of said wall of said combustor, said air blast tube being operable to deliver compressed air from said source into said combustor; and fuel supply means including a fuel supply ...

이 특허를 인용한 특허 피인용횟수: 14

  1. Teets, J. Michael. Annular combustor for use with an energy system. USP2005016845621.
  2. Lacy, Benjamin Paul; Ziminsky, Willy Steve; Johnson, Thomas Edward; Zuo, Baifang; York, William David; Uhm, Jong Ho. Bundled multi-tube nozzle for a turbomachine. USP2015099140454.
  3. Shah Nipulkumar. Combustor for a gas turbine engine. USP1998055746048.
  4. Biebel, Romain; Daguenet, Luc Henri Claude; Sandelis, Denis Jean Maurice. Configuration of dilution openings in a turbomachine combustion chamber wall. USP2011027891194.
  5. Stuttaford, Peter John; Kojovic, Aleksandar. Cyclone combustor. USP2003046543231.
  6. Lyons,Timothy M.. Engine exhaust gas passage flow orifice and method. USP2007127311090.
  7. Haynes, Joel Meier. Gas turbine combustor having counterflow injection mechanism. USP2013038387390.
  8. Haynes, Joel Meier. Gas turbine combustor having counterflow injection mechanism and method of use. USP2014078789375.
  9. Seymour Jeffrey L.. Gas turbine engine. USP1998035727378.
  10. Snyder, Timothy S.; Burd, Steven W.; McKinney, Randal G.; Titterton, George F.; Wong, Joey. Gas turbine engine systems and methods involving enhanced fuel dispersion. USP2015089115897.
  11. Snyder, Timothy S.; Burd, Steven W.; McKinney, Randal G.; Titterton, III, George F.. Gas turbine engine systems and methods involving enhanced fuel dispersion. USP20180910066836.
  12. Shekleton Jack R. ; Martin Curtis C.. Liquid fuel injector purge system. USP1999105966926.
  13. Ziminsky, Willy Steve; Johnson, Thomas Edward; Lacy, Benjamin Paul; York, William David; Uhm, Jong Ho; Zuo, Baifang. Premixed direct injection nozzle for highly reactive fuels. USP2013098539773.
  14. Stoia, Lucas John; Melton, Patrick Benedict; Johnson, Thomas Edward; Stevenson, Christian Xavier; Vanselow, John Drake; Westmoreland, James Harold. Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same. USP2016029267690.