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특허 상세정보

Combustion chamber for a gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/24   
미국특허분류(USC) 060/725; 060/039.83; 431/114; 181/220
출원번호 US-0280429 (2005-11-17)
등록번호 US-7448215 (2008-11-11)
우선권정보 GB-0427147.4(2004-12-11)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Taltavull,W. Warren
인용정보 피인용 횟수 : 11  인용 특허 : 2
초록

A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the chamber interior. The resonator neck is provided with at least cooling holes extending through its wall for improved damping and cooling, at least one of the holes is directed towards the resonator cavity.

대표
청구항

We claim: 1. A combustion chamber for a gas turbine engine comprising at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the interior of the combustion chamber, the neck having cooling holes extending through a wall thereof, at least one of the cooling holes having an axis that is directed towards the resonator cavity such that in use the cooling holes direct cooling air into the resonator cavity. 2. A combustion chamber according to claim 1, comprising at least two Helmholtz resonators. 3. A c...

이 특허를 인용한 특허 피인용횟수: 11

  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. Macquisten, Michael A; Moran, Anthony J; Whiteman, Michael; Carrotte, Jonathan F; Barker, Ashley G. Combustion chamber for a gas turbine engine. USP2010127857094.
  3. Huber, Andreas; Noiray, Nicolas; Schuermans, Bruno; Benz, Urs. Combustion device for a gas turbine. USP2018019857079.
  4. Huber, Andreas; Noiray, Nicolas; Schuermans, Bruno; Benz, Urs. Combustion device for a gas turbine configured to suppress thermo-acoustical pulsations. USP2015038991185.
  5. Schnell, Alexander; Noiray, Nicolas; Reinert, Felix; Lauffer, Diane; Schuermans, Bruno. Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators. USP2014098839624.
  6. Schilp, Reinhard. Cooling chamber for upstream weld of damping resonator on turbine component. USP2016089410484.
  7. Tonon, Devis; Bothien, Mirko Ruben. Damper of a gas turbine with a gap. USP20181110125987.
  8. Ikeda, Kazufumi; Mandai, Shigemi; Kawata, Yutaka; Aoyama, Kuniaki; Ono, Masaki; Tanaka, Katsunori. Gas turbine combustor and a gas turbine equipped therewith. USP2010117832211.
  9. Eroglu, Adnan; Freitag, Ewald; Rüdel, Uwe; Benz, Urs; Huber, Andreas. Gas turbine combustor including an acoustic damper device. USP2014018635874.
  10. 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.
  11. 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.