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특허 상세정보

Quench jet arrangement for annular rich-quench-lean gas turbine combustors

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-001/00    F02G-003/00   
미국특허분류(USC) 060/754;
출원번호 US-0947337 (2007-11-29)
등록번호 US-8127554 (2012-03-06)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Ingrassia Fisher & Lorenz, P.C.
인용정보 피인용 횟수 : 1  인용 특허 : 16
초록

An outer liner of a combustor of a gas turbine engine includes a plurality of liner regions arranged adjacent one another and separated by boundary lines; and a plurality of air admission holes formed in the liner regions. The air admission holes within each liner region form a V-pattern.

대표
청구항

1. A combustor for a turbine engine, comprising: an outer liner having a first group of air admission holes and defining a plurality of outer liner regions, each outer liner region being separated from an adjacent outer liner by an outer boundary line; an inner liner circumscribed by the outer liner and forming a combustion chamber therebetween, the inner liner having a second group of air admission holes and defining a plurality of inner liner regions, each inner liner region being separated from an adjacent inner liner region by an inner boundary line,...

이 특허에 인용된 특허 (16)

  1. Wright, E. Scott. Airflow modulation technique for low emissions combustors. USP2004126826913.
  2. Burrus David L. ; Johnson Arthur W. ; Mongia Hukam C.. Apparatus and method for rich-quench-lean (RQL) concept in a gas turbine engine combustor having trapped vortex cavity. USP2001096286298.
  3. Willis Jeffrey D. (Coventry GB2). Combustion apparatus for a gas turbine. USP1990014893475.
  4. Zupanc,Frank J.; Yankowich,Paul R.. Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions. USP2006067065972.
  5. Taylor Jack R. (Cincinnati OH). Low NOx combustor. USP1987104698963.
  6. Geza Vermes ; George Opdyke, Jr.. Low NOX gas turbine combustor liner. USP2002046378286.
  7. Hoke James B. ; Segalman Irving ; Siskind Kenneth S. ; Smith Reid D. C.. Low NOx combustor for gas turbine engine. USP2001066240731.
  8. Hoke James B. ; Mountz Daryl B. ; Olsen Howard ; Sonntag Robert M.. Low emissions can combustor with dilution hole arrangement for a turbine engine. USP2000086101814.
  9. Snyder, Timothy S.. Low emissions combustor for a gas turbine engine. USP2004116810673.
  10. Bernier, Daniel Francis Paul; Campion, Jean-Michel Jacques; Touchaud, Stéphane Henri Guy. Performance of a combustion chamber by multiple wall perforations. USP2010077748222.
  11. Feitelberg Alan S. ; Schmidt Mark Christopher ; Goebel Steven George. Rapid-quench axially staged combustor. USP1999125996351.
  12. Allen M. Danis ; Byron A. Pritchard, Jr. ; Keith K. Taylor ; Richard W. Stickles ; Willard J. Dodds ; Donald L. Gardner. Rich double dome combustor. USP2002116474070.
  13. Dudebout,Rodolphe; Kuhn,Terrel E.; Yankowich,Paul R.; Zupanc,Frank J.. Rich quick mix combustion system. USP2007037185497.
  14. Massarani Madhat. Rich-quench-lean combustor for use with a fuel having a high vanadium content and jet engine or gas turbine system havi. USP1998105819540.
  15. Schumacher,Jurgen C.; Critchley,Ian L.; Walhood,David G.. Temperature variance reduction using variable penetration dilution jets. USP2006027000400.
  16. Ansart Denis Roger Henri,FRX ; James Bruno,FRX ; Desaulty Michel Andre Albert,FRX ; Staessen Richard Emile,FRX. Turbomachine combustion chamber with inner and outer injector rows. USP2000066070412.