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특허 상세정보

Damper arrangement for reducing combustion-chamber pulsations

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/00   
미국특허분류(USC) 060/725; 431/114
출원번호 US-0988307 (2001-11-19)
우선권정보 DE-0058688 (2000-11-25)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Burns, Doane, Swecker & Mathis, L.L.P.
인용정보 피인용 횟수 : 19  인용 특허 : 3
초록

The invention relates to a damper arrangement for reducing combustion-chamber pulsations arising inside a gas turbine (1), having a combustion-chamber housing (8) which upstream comprises a front plate (2) with a plurality of individual burners (6) and damping elements (7, 7a, 7b) projecting through the front plate (2) and downstream is connected to a turbine stage (9) and is surrounded by a turbine housing (3) which comprises first openings (5a) which are adapted to the burners (6) and through which the burners (6) project upstream. The invention is cha...

대표
청구항

1. A damper arrangement for reducing combustion-chamber pulsations arising inside a gas turbine, comprising: a combustion-chamber housing, said combustion-chamber housing having a front plate at an upstream side; a plurality of individual burners and damping elements projecting through the front plate; said combustion-chamber housing being connected at a downstream side to a turbine stage and being surrounded by a turbine housing; said turbine housing having first openings through which the burners project in an upstream direction, and closable sec...

이 특허를 인용한 특허 피인용횟수: 19

  1. Portillo Bilbao, Juan Enrique; Rajaram, Rajesh; You, Danning; Spence, Kevin M.. Acoustic damping system for a combustor of a gas turbine engine. USP2016079400108.
  2. Wasif,Samer P.; Johnson,Clifford E.. Acoustic resonator with impingement cooling tubes. USP2008087413053.
  3. Slobodyanskiy, Ilya; Lipinski, John; Srinivasan, Shiva; Tretyakov, Dmitry. Acoustically stiffened gas turbine combustor supply. USP2014038661822.
  4. Sattinger,Stanley S.. Acoustically stiffened gas-turbine fuel nozzle. USP2008127464552.
  5. Alkabie,Hisham. Aerodynamic trip for a combustion system. USP2007127302802.
  6. Graf,Peter; Tschirren,Stefan; Wunderle,Helmar. Combustion chamber for a gas turbine. USP2008027331182.
  7. Macquisten,Michael A; Moran,Anthony J; Whiteman,Michael; Carrotte,Jonathan F; Barker,Ashley G; Goodwin,Martin S. Combustion chamber for a gas turbine engine. USP2008117448215.
  8. Bethke,Sven; Buchal,Tobias; Huth,Michael; Nimptsch,Harald; Prade,Bernd; Glessner,John Carl. Combustion chamber for a gas turbine with at least two resonator devices. USP2008027334408.
  9. Eroglu, Adnan; Riccius, Oliver; Knapp, Klaus; Flohr, Peter. Combustor with reduced carbon monoxide emissions. USP2010117827777.
  10. Lee, Ching-Pang; You, Danning; Schilp, Reinhard; Prakash, Chander. Damping resonator with impingement cooling. USP2017019546558.
  11. Commaret, Patrice Andre; Duval, Sylvain; Hernandez, Didier Hippolyte; Vuillemenot, Yann Francois Jean-Claude. Device for attaching a combustion chamber. USP2011108028530.
  12. Corr, Robert; Sykes, Peter; Struck, Bruno; Thomas, Kenneth G.; Braeutigam, Richard; Gauce, Danny; Krichever, Alexander; Phi, Vu; Caron, Timothy. Gas turbine combustor with mounting for Helmholtz resonators. USP2015038973365.
  13. Duge, Robert T.. Gas turbine engine having configurable bypass passage. USP2017099771945.
  14. Magni, Fulvio; Von Planta, Martin Andrea; Grimm, Frank; Nowak, Dariusz; Schaerer, Mischa. Helmholtz damper for a combustor of a gas turbine and a method for installing the helmholtz damper. USP2015028943825.
  15. Eroglu, Adnan. Helmholtz damper for gas turbine with cooling air flow. USP20180710018088.
  16. Proscia, William; Liljenberg, Scott A.; Roy, William J.; McCormick, Duane C.; Chipman, Christopher T.. Low pressure drop, low NOx, induced draft gas heaters. USP2015099127837.
  17. Harris, Ralph E.; Broerman, III, Eugene L.; Bourn, Gary D.. Side branch absorber for exhaust manifold of two-stroke internal combustion engine. USP2011017866147.
  18. Deffenbaugh, Danny; McKee, Robert; Nored, Marybeth. Tunable choke tube for pulsation control device used with gas compressor. USP2012028123498.
  19. Park, Roger James. Turbine engine fuel injector with helmholtz resonators. USP2012038127546.