• 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Acoustic damping system for a combustor of a gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F23R-003/60    F23R-003/00    F23M-020/00   
출원번호 US-0893441 (2013-05-14)
등록번호 US-9400108 (2016-07-26)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 0  인용 특허 : 23

An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing a...


1. A turbine engine with an acoustic clamping resonator system, comprising: a gas turbine engine combustor positioned downstream from a compressor and formed from at least one outer housing defining a combustor basket and at least one upstream wall that is attached to the at least one outer housing, wherein at least one fuel nozzle of a fuel nozzle assembly extends into the combustor;at least one resonator positioned within the gas turbine engine combustor at the at least one outer housing and extending circumferentially within the combustor;wherein the ...

이 특허에 인용된 특허 (23)

  1. Pandalai Raghavan P. (Cincinnati OH) Carter Bruce A. (West Chester OH) Hehmann Horst W. W. (Cincinnati OH). Acoustic damper for a gas turbine engine combustor. USP1997115685157.
  2. Borja,Mark Edward; Hendricks,Gavin Julian. Acoustic dampers. USP2008017322195.
  3. Wasif,Samer P.; Johnson,Clifford E.. Acoustic resonator with impingement cooling tubes. USP2008087413053.
  4. Sattinger,Stanley S.. Acoustically stiffened gas-turbine fuel nozzle. USP2008127464552.
  5. Davi Michael A. (Schenectady NY) Davis ; Jr. Lewis B. (Schenectady NY) Hopkins Edward P. (East Berne NY). Acoustically tuned combustor. USP1983104409787.
  6. Paschereit, Christian Oliver; Weisenstein, Wolfgang; Flohr, Peter; Polifke, Wolfgang. Apparatus for damping acoustic vibrations in a combustor. USP2003106634457.
  7. Keller Jakob J.,CHX. Burner with acoustically damped fuel supply system. USP2001106305927.
  8. Vincent, Thomas Alain Christian. Central body for a turbojet exhaust channel, turbojet. USP2011027886543.
  9. Bouty, Eric Jean-Louis; Dravet, Alain; Le Docte, Thierry Jacques Albert; Riou, Georges Jean Xavier; Vincent, Thomas Alain Christian. Central body of a turbojet nozzle. USP2011027891195.
  10. Macquisten, Michael A; Moran, Anthony J; Whiteman, Michael; Carrotte, Jonathan F; Barker, Ashley G. Combustion chamber for a gas turbine engine. USP2010127857094.
  11. 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.
  12. 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.
  13. Hellat, Jaan; Tschirren, Stefan; Stuber, Peter; Paschereit, Christian Oliver. Damper arrangement for reducing combustion-chamber pulsations. USP2003046546729.
  14. Huck Andr (Saint Just FRX) Kernilis Alain (Paris FRX) Druart Jean-Paul (Notre Dame de L\Isle FRX) Dorville Georges (Rouen FRX). Damping system for high frequency combustion instabilities in a combustion chamber. USP1994105353598.
  15. Gulati Anil (Cincinnati OH) Dean Anthony John (Scotia NY) Holmes David Graham (Schenectady NY) Voorhees Eayre Bruce (Sloansville NY). Dynamics free low emissions gas turbine combustor. USP1997075644918.
  16. Ikeda,Kazufumi; Ishiguro,Tatsuo; Tanaka,Katsunori; Tanimura,Satoshi. Gas turbine combustor. USP2006087089741.
  17. Ikeda, Kazufumi; Mandai, Shigemi; Kawata, Yutaka; Aoyama, Kuniaki; Ono, Masaki; Tanaka, Katsunori. Gas turbine combustor and a gas turbine equipped therewith. USP2010117832211.
  18. Gerendás, Miklós; Ebel, Michael. Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber. USP2011047926278.
  19. Sattinger, Stanley S.. Method of suppressing combustion instabilities using a resonator adopting counter-bored holes. USP2009067549506.
  20. Sattinger, Stanley S.; Darling, Douglas Dean; Holbert, Roy Kyle; Kepes, William E.. Modular resonators for suppressing combustion instabilities in gas turbine power plants. USP2003036530221.
  21. Bellucci,Valter; Flohr,Peter; Paschereit,Christian Oliver; Schuermans,Bruno; Tabacco,Daniele. Reheat combustion system for a gas turbine. USP2006016981358.
  22. Johnson, Clifford E.; Wasif, Samer P.. Resonator device at junction of combustor and combustion chamber. USP2010097788926.
  23. Park, Roger James. Turbine engine fuel injector with helmholtz resonators. USP2012038127546.