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 PDFInfo
- 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
Links
Images
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").
Landscapes
- 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)
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 |
Family
ID=34925277
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04013404A Expired - Lifetime EP1605209B1 (fr) | 2004-06-07 | 2004-06-07 | Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP1605209B1 (fr) |
DE (1) | DE502004011481D1 (fr) |
Cited By (16)
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 |
WO2013029984A2 (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 |
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102019204746A1 (de) | 2019-04-03 | 2020-10-08 | Siemens Aktiengesellschaft | Hitzeschildkachel mit Dämpfungsfunktion |
Citations (5)
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 |
-
2004
- 2004-06-07 EP EP04013404A patent/EP1605209B1/fr not_active Expired - Lifetime
- 2004-06-07 DE DE502004011481T patent/DE502004011481D1/de not_active Expired - Lifetime
Patent Citations (5)
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)
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 |
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 |
WO2013029984A2 (fr) | 2011-09-01 | 2013-03-07 | Siemens Aktiengesellschaft | Chambre de combustion pour une installation de turbine à gaz |
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***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***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 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE10058688B4 (de) | Dämpferanordnung zur Reduktion von Brennkammerpulsationen | |
EP1605209B1 (fr) | Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques | |
EP0985882B1 (fr) | Amortissement des vibrations dans des combusteurs | |
DE102010037078B4 (de) | Akustisch versteifte Gasturbinenbrennkammerzuführung | |
DE60105531T2 (de) | Gasturbinenbrennkammer, Gasturbine und Düsentriebwerk | |
EP1004823B1 (fr) | Dispositif d'amortissement pour la réduction de l'amplitude d'oscillation d'ondes acoustiques pour un brûleur | |
EP1738112B1 (fr) | Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs | |
DE19640980B4 (de) | Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer | |
WO2003074936A1 (fr) | Turbine a gaz | |
DE102008037480A1 (de) | Mager vorgemischte Dual-Fuel-Ringrohrbrennkammer mit Radial-Mehrring-Stufendüse | |
EP0687860A2 (fr) | Chambre de combustion à allumage automatique | |
EP2500648B1 (fr) | Chambre de combustion de turbines à gaz | |
DE102008016931A1 (de) | System zur Reduktion der Brennkammerdynamik | |
DE102005062284A1 (de) | Brennkammer für eine Gasturbine | |
EP2354659A1 (fr) | Amortisseur de Helmholtz pour l'intégration dans la chambre de combustion d'une turbine à gaz et procédé d'intégration d'un tel amortisseur de Helmholtz | |
EP0971172B1 (fr) | Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse | |
WO2013029981A1 (fr) | Chambre de combustion pour une installation de turbine à gaz | |
EP2187125A1 (fr) | Dispositif et procédé destinés à l'amortissement d'oscillations de combustion | |
EP2417394B1 (fr) | Chambre de combustion dotée d'un amortisseur de helmholtz | |
WO2010149420A1 (fr) | Agencement de chambre de combustion pour l'amortissement de vibrations thermo-acoustiques, turbine à gaz et procédé pour utiliser une telle turbine à gaz | |
EP1624251B1 (fr) | Dispositif pour atténuer les oscillations acoustiques dans les chambres combustion avec fréquence de résonance ajustable | |
EP2295858A1 (fr) | Stabilisation de la flamme d'un brûleur | |
EP1596130B1 (fr) | Appareil pour absorber les oscillations thermo-acoustiques dans une chambre de combustion, présentant une fréquence de résonance variable | |
EP2270397A1 (fr) | Chambre de combustion de turbine à gaz et turbine à gaz | |
WO2008138828A1 (fr) | Dispositif et procédé de mesure de vibrations acoustiques dans un écoulement fluidique et turbine à gaz équipée d'un dispositif de ce type |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL HR LT LV MK |
|
17P | Request for examination filed |
Effective date: 20060410 |
|
17Q | First examination report despatched |
Effective date: 20060714 |
|
AKX | Designation fees paid |
Designated state(s): CH DE GB IT LI |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F23R 3/60 20060101ALI20100127BHEP Ipc: F23R 3/00 20060101AFI20100127BHEP Ipc: F23R 3/06 20060101ALI20100127BHEP |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE GB IT LI |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: NV Representative=s name: SIEMENS SCHWEIZ AG |
|
REF | Corresponds to: |
Ref document number: 502004011481 Country of ref document: DE Date of ref document: 20100916 Kind code of ref document: P |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20110506 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502004011481 Country of ref document: DE Effective date: 20110506 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20120626 Year of fee payment: 9 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20130607 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PCOW Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE) |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20180614 Year of fee payment: 15 Ref country code: DE Payment date: 20180820 Year of fee payment: 15 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 20180910 Year of fee payment: 15 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502004011481 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20190607 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190607 Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200101 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190630 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190630 |