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특허 상세정보

Gas turbine engine having a multi-stage multi-plane combustion system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-003/00   
미국특허분류(USC) 060/746; 060/737
출원번호 US-0171684 (2002-06-17)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Sterne, Kessler, Goldstein & Fox PLLC
인용정보 피인용 횟수 : 21  인용 특허 : 102
초록

A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner...

대표
청구항

20000224, 2000-512986

이 특허에 인용된 특허 (102)

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  3. Toronto, David Kaylor; Kim, Kwanwoo; Khan, Abdul Rafey; Flamand, Luis. Combustor with fuel staggering for flame holding mitigation. USP2016089416974.
  4. Toronto, David Kaylor; Kim, Kwanwoo; Khan, Abdul Rafey; Flamand, Luis. Combustor with fuel staggering for flame holding mitigation. USP2014108863525.
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  20. Mehring, Carsten Ralf; Peffley, James. Symmetric fuel injection for turbine combustor. USP2015069062609.
  21. Hawie, Eduardo; Davenport, Nigel. Two-stage combustor for gas turbine engine. USP2016019243802.