EP1605209A1 - Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques - Google Patents

Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques Download PDF

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Publication number
EP1605209A1
EP1605209A1 EP04013404A EP04013404A EP1605209A1 EP 1605209 A1 EP1605209 A1 EP 1605209A1 EP 04013404 A EP04013404 A EP 04013404A EP 04013404 A EP04013404 A EP 04013404A EP 1605209 A1 EP1605209 A1 EP 1605209A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
resonator
combustion
chamber according
helmholtz resonator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP04013404A
Other languages
German (de)
English (en)
Other versions
EP1605209B1 (fr
Inventor
Sven Dr. Bethke
Tobias Dr. Buchal
Michael Dr. Huth
Harald Nimptsch
Bernd Dr. Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to DE502004011481T priority Critical patent/DE502004011481D1/de
Priority to EP04013404A priority patent/EP1605209B1/fr
Publication of EP1605209A1 publication Critical patent/EP1605209A1/fr
Application granted granted Critical
Publication of EP1605209B1 publication Critical patent/EP1605209B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the present invention relates to a combustion chamber with a Damping device for damping thermoacoustic Vibrations, especially for a gas turbine, and a Gas turbine with such a combustion chamber.
  • a gas turbine plant comprises e.g. a compressor, one Combustion chamber and a turbine.
  • the compressor is compressed sucked air, which subsequently a fuel is added.
  • the combustion chamber is the mixture burned, with the combustion exhaust gases supplied to the turbine become. From the turbine, the combustion exhaust gases become thermal Deprived of energy and converted into mechanical energy.
  • the cooling air also serves to block openings, for example, gaps between two adjoining heat shield elements a combustion chamber, i. to prevent that hot gas from the combustion chamber enters the opening. Thereby the air supply to the burner is reduced and the emission Pollutants, such as nitrogen oxides, are increasing.
  • thermoacoustic vibrations can increase. It can to a swelling interaction between thermal and acoustic interference come, the high loads the combustion chamber and in turn cause rising emissions can.
  • a Helmholtz resonator Usually includes a volume with air in it or another gas. The volume is followed Tube, the so-called. Resonatorrohr, in which also air or gas and that opens into the combustion chamber.
  • the air or the gas in the volume and in the resonator tube form a spring-mass system, wherein the air or the gas in the volume Spring and the air or the gas in the resonator tube the mass forms.
  • thermo-acoustic vibrations which essentially standing waves can be so for frequencies that correspond to the resonant frequency of the Helmholtz resonator or in their vicinity, are effectively suppressed.
  • the first object is achieved by a combustion chamber solved according to claim 1, the second object by a gas turbine according to claim 13.
  • the dependent claims contain advantageous developments of the invention.
  • a combustion chamber according to the invention comprises at least one cooling combustion chamber element and at least one damping device for damping thermoacoustic vibrations with a mouth open to the combustion chamber. It stands out characterized in that the mouth into the combustion chamber element to be cooled is integrated.
  • the mouth in the inventive the combustion chamber associated with a blocking air supply be. This then serves as a cooling air supply for the cooling of the combustion chamber element to be cooled.
  • a Be assigned fuel supply such that the sealing air Fuel is added. The addition of fuel to the blocking air leads to a lowering of the combustion temperature in the main burner and thus to a reduction of Pollutant content of the combustion gases.
  • the combustion chamber a combustion chamber wall, which is a combustion chamber shell and a means of cooling to be cooled fasteners on the combustion chamber shell fastened combustion chamber lining, on.
  • the combustion chamber lining may, for example, be a heat shield, in particular a ceramic or metallic heat shield.
  • the mouth of the at least one damping device is in this embodiment in a fastener for fastening the combustion chamber lining integrated on the combustion chamber shell.
  • that is to be cooled combustion chamber element as a fastener for Attach the combustion chamber lining formed.
  • the fasteners anyway there are and a cooling require integrating the muzzle into a fastener only a redesign of the fastener, For example, by fastening screws with an axial Bore or other axial passage opening be provided so that they serve as the mouth of the damping element can serve. Further transformations of the interior of the Combustion chamber are not necessary in this embodiment.
  • the fastener can also as a fastening element, which at least one sliding seat device includes, be configured.
  • a sliding seat device is often located, for example, at the transition from the so-called "Basket” to the so-called “Transitionpiece” in a silo-burning chamber.
  • the damping device can also at the transition from the Combustion chamber be arranged to the first Leitschauffel #2. As a rule, quite high blocking air flows are needed there. This applies to ring combustion chambers and also for silo separation chambers.
  • the damping element be configured in particular such that the to be cooled Combustor element part of the damping device forms.
  • the to be cooled Combustor element part of the damping device forms can be a fixing screw with axial Through hole the resonator tube of a Helmholtz resonator form.
  • the damping device as a Helmholtz resonator, in particular as a Helmholtz resonator implemented with variable resonance frequency.
  • the variability of the resonance frequency thereby be achieved that the volume of the Helmholtz resonator is designed changeable.
  • a volume change can e.g. achieved via an adjustable rear wall of the resonator become.
  • the Helmholtz resonator may also include multiple orifices, each integrated into a combustion chamber element to be cooled are.
  • multiple orifices each integrated into a combustion chamber element to be cooled are.
  • the Damping device as ⁇ / 4 pipe, so as a pipe with a quarter of the wavelength of the vibration to be damped formed.
  • a gas turbine according to the invention comprises at least one inventive Combustion chamber.
  • Fig. 1 shows a detail as a first embodiment from the combustion chamber wall of an inventive Combustion chamber in a highly schematic representation.
  • Fig. 2 shows a view of the combustion chamber wall of a second Embodiment of the invention of the combustion chamber inside seen here.
  • FIG. 3 shows a side view of that shown in FIG. 2 Combustion chamber wall.
  • FIG. 1 is as a first embodiment of the invention a combustion chamber of a gas turbine according to the invention shown.
  • the figure shows a section of the combustion chamber wall 1, which is a combustion chamber shell 3 and a metallic Heat shield 4 includes.
  • the metallic heat shield 4 is composed of a number of heat shield elements 2, each by means of a screw 7 as a fastener fixed to a connection point 5 on the combustion chamber shell 3 are. Set the screws 7 like the heat shield elements 2 by means of cooling air to be cooled combustion chamber elements.
  • At least one damping device for damping of acoustic vibrations in the combustion chamber this is with at least one damping device, which in the present embodiment as opening into the combustion chamber Helmholtz resonator 6 is formed, equipped.
  • the Helmholtz resonator 6 is in the region of a connection point 5 attached to the combustion chamber wall 1. He is using a fastener or more fasteners (not shown) on the combustion chamber wall. 1 held.
  • the Helmholtz resonator 6 by means of the screw 7 at the combustion chamber wall 1 to keep. In this case, the serves Screw 7 then both for holding the heat shield element. 2 as well as for holding the Helmholtz resonator 6, so that a additional fastening element for holding the Helmholtz resonator 6 is not necessary.
  • the Helmholtz resonator 6 comprises a resonator 15 and a resonator tube, also called resonator neck.
  • the resonator tube is in the present embodiment of the screw 7 formed, which for this purpose a through hole. 8 having.
  • One end 9 of the through hole 8 opens into the Resonator space 15.
  • the other end 10 of the through hole. 8 opens into the combustion chamber and forms the mouth of the Helmholtz resonator 6 in the combustion chamber.
  • the damping effect Helmholtz resonator 6 is based on the fact that the in the resonator 15 and in the resonator tube 8 located air how a spring-mass system behaves.
  • the resonator 6 in Substantially cylindrically symmetric to the screw 7 executed.
  • the resonant frequency of the Helmholtz resonator 6 can be adjusted. For example, leads to an increase in the volume V of the resonator cavity 15 or the length L of the screw 7 to a reduced Resonance frequency. An enlargement of the cross-sectional area F of Through hole 8, however, leads to an increased resonant frequency.
  • the rear wall 17 of the Helmholtz resonator 6 adjustable be educated. On the cylindrical side wall 12 of the Helmholtz resonator 6 is then, for example, a thread 16 present, in which a matching mating thread of the rear wall 17th intervenes.
  • the volume V of the resonator 15 and thus the Resonator frequency can be changed in the desired manner. But it is also possible, the volume by replacing the resonator 15 against a resonator 15 with another volume to change.
  • the length L of Screw and / or the cross-sectional area F of the through hole 8 are changed.
  • a screw 7 are used, whose Bore 8 has a larger cross-sectional area F than previously used screw 7 has. It can be for the same purpose but also a screw 7 with a shorter length L used become.
  • the resonance frequency of Helmholtz resonator 6 can be influenced.
  • the resonator 15 on the cold side i. facing away from the combustion chamber Outside the combustion chamber shell 3 mounted and protrudes into the Compressor plenum 20 into it.
  • To provide an air supply for a To allow impingement cooling of the heat shield elements 2 are between the resonator chamber 15 and the outside of the combustion chamber shell 3 locally mounted spacers 19, the one Distance between the combustion chamber shell 3 and the resonator chamber 15, thus ensuring a flow from the pressurized Cooling air between the combustion chamber shell 3 and the Resonatorraum 15 allow.
  • impingement cooling holes 14 Cooling air can then from the Kompressplplenum 20 out along the Flow paths 13 facing away from the combustion chamber interior Side, the so-called.
  • Cold side of the heat shield elements 2 passed be where they are for an impingement air cooling of the heat shield elements 2 cares.
  • the impingement air flows after hitting the cold sides along the flow paths 23 through gaps between adjacent heat shield elements 2 in the combustion chamber a, whereby the column against penetration of hot Gas of the combustion chamber locks.
  • the cooling of the screw 7 takes place together with the lock the mouth 10 of the Helmholtz resonator 6 against ingress of hot gas.
  • the air first flows out of the compressor plenum 20 through the openings 18 (which the sealing air supply form) in the rear wall 17 of the resonator 15 in the resonator 15 and then through the through hole 8 of the Screw 7 in the combustion chamber (flow path 11).
  • the cooling of Helmholtz resonator 6 and screw 7 with the same cooling air, the proportion of cooling air, the passed the burner, opposite a separate Cooling of Helmholtz resonator 6 and screw 7 as needed would be if the screw 7 is not at the same time as a resonator tube served, be reduced.
  • FIGS. 2 and 3 a second embodiment is strong shown schematically. Same or similar components for simplicity and better comparability with the same reference numerals as in the first embodiment Mistake.
  • Fig. 2 shows, seen from the combustion chamber interior, a Section of a combustion chamber 1, with metallic Heat shield plates 21, 22 lined as heat shield elements is.
  • Fig. 3 shows a section through the combustion chamber wall 1 along the line A - A.
  • the heat shield plates 21, 22 are at connection points 5 screwed by screws 7 with the combustion chamber shell 3.
  • Helmholtz resonators 6 are arranged at the connection points 5, the means of screws 7 on the combustion chamber wall 1 are fixed.
  • a through hole or through hole 8 in the screws 7 serves as in the first embodiment as a resonator tube of the respective Helmholtz resonator 6. For the sake of simplicity, only one is shown in FIG the Helmholtz resonators 6 shown.
  • a resonator 15 over several Screws 7 expands.
  • all screws 7, over which the resonator 15 extends, with through holes be provided and thus form resonator tubes.
  • only a few or even only one only one of the screws 7, over which the resonator 15 extends to be provided with a through hole 8.
  • the remaining Screws 7 then serve only as mounting screws for the heat shield plates or for the heat shield plates 21, 22 and the Helmholtz resonator.
  • a controller (not shown) is provided by means of of which the adjustment of the resonator volume are controlled can.
  • an automatic adjustment or regulation is possible. It can, for example, an electric motor, a hydraulic Adjusting device or a pneumatic adjusting device used become. Through a controlled automatic adjustment is the effort for subsequent adjustment of the resonator frequency kept very low. The scheme can done online during operation. With a fully automatic Regulation can be continuous or in certain Time intervals adjustment to the strongest vibration frequency respectively.
  • an altered fuel composition reacts and a Adjustment of the resonant frequency can be performed.
  • the simple one Adjustability is particularly advantageous in the Prototype testing and also during the commissioning of a gas turbine.
  • a significant advantage of easy adjustability does not just result from the operation with different ones Fuels, but also in widely different Operating conditions, caused e.g. through significant changes the ambient temperature.
  • a Helmholtz resonator 6 by replacing the screw with through hole switched off against a screw without through hole become.
  • the resonator 6 also completely be removed.
  • the invention is particularly suitable for use in Ring combustion chambers with metallic heat shields or at the so-called inlet shells of the combustion chambers with ceramic Heat shields ("stones").

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
EP04013404A 2004-06-07 2004-06-07 Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques Not-in-force EP1605209B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE502004011481T DE502004011481D1 (de) 2004-06-07 2004-06-07 Brennkammer mit einer Dämpfungseinrichtung zur Dämpfung von thermoakustischen Schwingungen
EP04013404A EP1605209B1 (fr) 2004-06-07 2004-06-07 Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04013404A EP1605209B1 (fr) 2004-06-07 2004-06-07 Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques

Publications (2)

Publication Number Publication Date
EP1605209A1 true EP1605209A1 (fr) 2005-12-14
EP1605209B1 EP1605209B1 (fr) 2010-08-04

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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1752637A2 (fr) 2005-08-10 2007-02-14 United Technologies Corporation Architecture pour un revêtement acoustique
EP1816357A1 (fr) * 2006-02-02 2007-08-08 Siemens Aktiengesellschaft Vis pour un environnement chargé thermiquement
EP1862739A2 (fr) 2006-06-01 2007-12-05 Rolls-Royce plc Chambre de combustion pour un moteur de turbine à gaz
EP1811143A3 (fr) * 2005-08-10 2009-10-28 United Technologies Corporation Revêtement acoustique avec refroidissement en dérivation
EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
CH700799A1 (de) * 2009-04-11 2010-10-15 Alstom Technology Ltd Brennkammer mit Helmholtzdämpfer für eine Gasturbine.
EP2299177A1 (fr) * 2009-09-21 2011-03-23 Alstom Technology Ltd Chambre de combustion de turbine à gaz
DE102011081962A1 (de) 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Brennkammer für eine Gasturbinenanlage
WO2013029984A2 (fr) 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
US8991185B2 (en) 2010-05-03 2015-03-31 Alstom Technology Ltd. Combustion device for a gas turbine configured to suppress thermo-acoustical pulsations
WO2016089341A1 (fr) * 2014-12-01 2016-06-09 Siemens Aktiengesellschaft Résonateurs comprenant des tubes de mesure interchangeables pour des turbines à gaz
WO2017097606A1 (fr) * 2015-12-08 2017-06-15 Siemens Aktiengesellschaft Chambre de combustion munie d'un résonateur
EP2317227A3 (fr) * 2009-10-28 2017-09-13 MAN Diesel & Turbo SE Brûleur pour une turbine et turbine à gaz en étant équipée
EP3410014A1 (fr) * 2017-05-31 2018-12-05 Ansaldo Energia S.p.A. Support de brique pour chambre de combustion d'une turbine à gaz
WO2021050836A1 (fr) * 2019-09-12 2021-03-18 General Electric Company Système et procédé pour amortisseurs acoustiques à volumes multiples dans un panneau avant de chambre de combustion
EP4071409A1 (fr) * 2021-04-06 2022-10-12 Raytheon Technologies Corporation Agencement de fixation de panneau de chambre de combustion cmc

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019204746A1 (de) 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Hitzeschildkachel mit Dämpfungsfunktion

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
WO2003023281A1 (fr) * 2001-09-07 2003-03-20 Alstom Technology Ltd Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
DE10325691A1 (de) * 2002-06-26 2004-01-22 Alstom (Switzerland) Ltd. Wiederaufheizverbrennungssystem für eine Gasturbine
US20040093872A1 (en) * 2002-08-16 2004-05-20 Peter Tiemann Internally coolable screw
EP1434006A2 (fr) * 2002-12-23 2004-06-30 Rolls-Royce Plc Chambre de combustion pour turbine à gaz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
WO2003023281A1 (fr) * 2001-09-07 2003-03-20 Alstom Technology Ltd Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
DE10325691A1 (de) * 2002-06-26 2004-01-22 Alstom (Switzerland) Ltd. Wiederaufheizverbrennungssystem für eine Gasturbine
US20040093872A1 (en) * 2002-08-16 2004-05-20 Peter Tiemann Internally coolable screw
EP1434006A2 (fr) * 2002-12-23 2004-06-30 Rolls-Royce Plc Chambre de combustion pour turbine à gaz

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1752637A3 (fr) * 2005-08-10 2009-10-28 United Technologies Corporation Architecture pour un revêtement acoustique
EP1811143A3 (fr) * 2005-08-10 2009-10-28 United Technologies Corporation Revêtement acoustique avec refroidissement en dérivation
EP1752637A2 (fr) 2005-08-10 2007-02-14 United Technologies Corporation Architecture pour un revêtement acoustique
EP1816357A1 (fr) * 2006-02-02 2007-08-08 Siemens Aktiengesellschaft Vis pour un environnement chargé thermiquement
WO2007088098A1 (fr) * 2006-02-02 2007-08-09 Siemens Aktiengesellschaft Vis destinee a etre utilisee dans des environnements thermiquement sollicites
JP2009525437A (ja) * 2006-02-02 2009-07-09 シーメンス アクチエンゲゼルシヤフト 熱的に負荷された環境で使用するためのボルト
US7857094B2 (en) 2006-06-01 2010-12-28 Rolls-Royce Plc Combustion chamber for a gas turbine engine
EP1862739A2 (fr) 2006-06-01 2007-12-05 Rolls-Royce plc Chambre de combustion pour un moteur de turbine à gaz
EP1862739A3 (fr) * 2006-06-01 2008-02-20 Rolls-Royce plc Chambre de combustion pour un moteur de turbine à gaz
EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
CH700799A1 (de) * 2009-04-11 2010-10-15 Alstom Technology Ltd Brennkammer mit Helmholtzdämpfer für eine Gasturbine.
WO2010115980A3 (fr) * 2009-04-11 2011-10-20 Alstom Technology Ltd. Chambre de combustion dotée d'un amortisseur de helmholtz
AU2010233724B2 (en) * 2009-04-11 2015-06-18 General Electric Technology Gmbh Combustion chamber having a helmholtz damper
EP2299177A1 (fr) * 2009-09-21 2011-03-23 Alstom Technology Ltd Chambre de combustion de turbine à gaz
WO2011032959A1 (fr) * 2009-09-21 2011-03-24 Alstom Technology Ltd Chambre de combustion d'une turbine à gaz
US8635874B2 (en) 2009-09-21 2014-01-28 Alstom Technology Ltd Gas turbine combustor including an acoustic damper device
EP2317227A3 (fr) * 2009-10-28 2017-09-13 MAN Diesel & Turbo SE Brûleur pour une turbine et turbine à gaz en étant équipée
US9857079B2 (en) 2010-05-03 2018-01-02 Ansaldo Energia Ip Uk Limited Combustion device for a gas turbine
US8991185B2 (en) 2010-05-03 2015-03-31 Alstom Technology Ltd. Combustion device for a gas turbine configured to suppress thermo-acoustical pulsations
WO2013029984A2 (fr) 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
WO2013029981A1 (fr) 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
DE102011081962A1 (de) 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Brennkammer für eine Gasturbinenanlage
WO2016089341A1 (fr) * 2014-12-01 2016-06-09 Siemens Aktiengesellschaft Résonateurs comprenant des tubes de mesure interchangeables pour des turbines à gaz
US9988958B2 (en) 2014-12-01 2018-06-05 Siemens Aktiengesellschaft Resonators with interchangeable metering tubes for gas turbine engines
WO2017097606A1 (fr) * 2015-12-08 2017-06-15 Siemens Aktiengesellschaft Chambre de combustion munie d'un résonateur
EP3410014A1 (fr) * 2017-05-31 2018-12-05 Ansaldo Energia S.p.A. Support de brique pour chambre de combustion d'une turbine à gaz
WO2021050836A1 (fr) * 2019-09-12 2021-03-18 General Electric Company Système et procédé pour amortisseurs acoustiques à volumes multiples dans un panneau avant de chambre de combustion
CN114402167A (zh) * 2019-09-12 2022-04-26 通用电气公司 用于燃烧室前板中有多个体积的声学阻尼器的系统和方法
US11506382B2 (en) 2019-09-12 2022-11-22 General Electric Company System and method for acoustic dampers with multiple volumes in a combustion chamber front panel
CN114402167B (zh) * 2019-09-12 2023-11-03 通用电气公司 用于燃烧室前板中有多个体积的声学阻尼器的系统和方法
EP4071409A1 (fr) * 2021-04-06 2022-10-12 Raytheon Technologies Corporation Agencement de fixation de panneau de chambre de combustion cmc
US11698192B2 (en) 2021-04-06 2023-07-11 Raytheon Technologies Corporation CMC combustor panel attachment arrangement

Also Published As

Publication number Publication date
DE502004011481D1 (de) 2010-09-16
EP1605209B1 (fr) 2010-08-04

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