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특허 상세정보

High altitude starting two-stage fuel injection apparatus

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F23R-003/34   
미국특허분류(USC) 60/3936 ; 60/738 ; 60/746
출원번호 US-0970101 (1992-11-02)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 13  인용 특허 : 0
초록

Difficulties in achieving reliable starts in gas turbine engines operating at high altitude are avoided in a gas turbine engine including a rotary compressor (10), a rotary turbine wheel (12) coupled to the compressor (10) to drive the same, and a nozzle (42) for directing gases of combustion against the turbine wheel (12). An annular combustor (34) has an outlet (40) connected to the nozzle (42) and an opposed dome (38) that is axially spaced from the outlet (40). At least three sets of air injection openings (80, 92, 100) are axially spaced from one an...

대표
청구항

A gas turbine engine comprising: a rotary compressor; a rotary turbine wheel coupled to said compressor to drive the same; a nozzle for directing gases of combustion against said turbine wheel; an annular combustor having an outlet connected to said nozzle and an opposed dome axially spaced from said outlet; at least three sets of air injector openings, each set axially spaced from one another with one set in close proximity to said dome; fuel injectors associated with two of said sets including said one set and the other of said sets that is nearest sai...

이 특허를 인용한 특허 피인용횟수: 13

  1. Teets, J. Michael. Annular combustor for use with an energy system. USP2005016845621.
  2. Toqan, Majed; Gregory, Brent Allan; Regele, Jonathan David; Yamane, Ryan Sadao. Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines. USP2015119181812.
  3. Shah Nipulkumar. Combustor for a gas turbine engine. USP1998055746048.
  4. Harris, Mark M.. Combustor system for an expendable gas turbine engine. USP2005086931862.
  5. Biebel, Romain; Daguenet, Luc Henri Claude; Sandelis, Denis Jean Maurice. Configuration of dilution openings in a turbomachine combustion chamber wall. USP2011027891194.
  6. Robert Paul Czachor. Gas injector system and its fabrication. USP2002086435816.
  7. Seymour Jeffrey L.. Gas turbine engine. USP1998035727378.
  8. Willis, Jeffrey W.; Pont, Guillermo; Toby, Benjamin E.; McKeirnan, Jr., Robert D.. Gas turbine engine having a multi-stage multi-plane combustion system. USP2004026684642.
  9. Jeffery W. Willis ; Guillermo Pont ; Benjamin E. Toby ; Robert D. McKeirnan, Jr.. Multi-stage multi-plane combustion system for a gas turbine engine. USP2002096453658.
  10. Toqan, Majed; Gregory, Brent Allan; Regele, Jonathan David; Yamane, Ryan Sadao. Tangential and flameless annular combustor for use on gas turbine engines. USP2015079091446.
  11. Toqan, Majed; Gregory, Brent Allan; Regele, Jonathan David; Yamane, Ryan Sadao. Tangential annular combustor with premixed fuel and air for use on gas turbine engines. USP2015069052114.
  12. Toqan, Majed; Gregory, Brent Allan; Yamane, Ryan Sadao; Regele, Jonathan David. Tangential combustor with vaneless turbine for use on gas turbine engines. USP2014128904799.
  13. Wiebe, David J.. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine. USP2017119810434.