EP0974788A1 - Dispositif d'atténuation adaptée de bruit dans une turbomachine - Google Patents
Dispositif d'atténuation adaptée de bruit dans une turbomachine Download PDFInfo
- Publication number
- EP0974788A1 EP0974788A1 EP98810714A EP98810714A EP0974788A1 EP 0974788 A1 EP0974788 A1 EP 0974788A1 EP 98810714 A EP98810714 A EP 98810714A EP 98810714 A EP98810714 A EP 98810714A EP 0974788 A1 EP0974788 A1 EP 0974788A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- helmholtz resonator
- combustion chamber
- volume
- fuel
- flow channel
- 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
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/96—Preventing, counteracting or reducing vibration or noise
-
- 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
Definitions
- the invention relates to a device for targeted sound attenuation within a turbomachine with a combustion chamber, into which a compressible medium, preferably air, is fed via a flow channel, in which the compressible medium is flammable with the addition of fuel, and a Helmholtz resonator volume, which is connected to the flow channel in the flow direction before entering the combustion chamber.
- a compressible medium preferably air
- a Helmholtz resonator volume which is connected to the flow channel in the flow direction before entering the combustion chamber.
- Precautions for sound attenuation of the aforementioned type are for the operation of gas turbine plants with a view to improving the combustion process vital within the combustion chamber. So occur when operating gas turbine systems in certain areas of the supply air and Fuel gas flow as well as acoustic within the combustion chamber Vibration phenomena, which change depending on the load conditions, under which the gas turbine is operated, train more or less strongly. For Suppression of such acoustic vibrations became measures on the design and undertake the design of such thermodynamic machines, but the effects achieved with it were of little success, in particular, it was not possible to have thermoacoustically induced instabilities within of gas flow completely suppressing, causing oscillations that significantly impair the operation of gas turbine plants.
- Oscillations occurring in the flow of gas turbines are not only capable permanently influence the combustion process of the air-gas mixture, but transmit the pressure waves propagating in the gaseous medium also refer to the housing parts immediately surrounding the flow paths the gas turbine plant, which due to temperature and pressure loads the mechanical oscillating vibrations another, significant Material fatigue criteria are subject, which last but not least the service life a gas turbine plant is decisively influenced.
- Helmholtz resonators have become known as sound-absorbing elements, which are used within the inflow of gas turbines.
- the use of Helmholtz resonators in gas turbines is in a contribution by J. J. Keller and E. Zauner, "On the Use of Helmholtz-Resonators as Sound Attentuators ", Z. Appl. Math. Phys., 46 (1995), pages 297 to 326.
- Helmholtz resonators are characterized in particular by the fact that they have a so-called Have Helmholtz resonator volume through which the flow flow passes through.
- the Helmholtz resonator volume also has at least a flow inlet and an outlet channel, the flow channel diameter are dimensioned smaller than the flow cross section within the Helmholtz resonator volume.
- Helmholtz resonators be carried out in the respective flow systems, but the well-known Helmholtz resonator systems offer due to their unique specified size and design only limited possibilities individual Frequency adjustments to set a desired low resonance frequency, typically less than 100 Hz.
- the invention has for its object a device for targeted sound attenuation according to a turbomachine with a combustion chamber the preamble of claim 1 using a Helmholtz resonator to further develop in such a way that measures for noise reduction are avoided of thermoacoustic oscillations within the flow flow with the simplest possible means can be further improved. Furthermore, these should Measures are associated with the lowest possible investment.
- soundproofing is intended to offer expanded options, desired Resonance frequency shifts of the damper elements in a large Range to small frequencies and also the size the Helmholtz resonators as small as possible.
- a first inventive concept for sound attenuation within a Vibration machine with a combustion chamber sees an injector assembly within the Helmholtz resonator volume before entering the flow channel before the Helmholtz resonator volume connects to the combustion chamber. From the injector assembly becomes liquid, preferably water, in the direction of the flow channel atomized into the finest liquid droplets to the combustion chamber, so that before entry forms a liquid-air mixture in the combustion chamber.
- This device is based on the idea of the speed of sound within the flow channel by targeted introduction of a To change the liquid-air mixture in order to change the resonance behavior of the to influence the entire sound system in a targeted manner.
- the injector assembly is formed such that the liquid droplet size by appropriate nozzle variation and the degree of atomization regulated in the desired manner can be. Thanks to the injection nozzle arrangement, which can be adjusted over a wide range it is possible through the targeted introduction of an additional mass flow in the form of liquid drops the sound propagation behavior within to influence the flow channel and individually to the existing flow geometries to adapt so that the occurrence of thermoacoustic Oscillations can be effectively countered. So it succeeds the Tuning silencers also to very low vibration frequencies
- Another advantage is the targeted introduction of a liquid-gas mixture connected within the Helmholtz resonator volume protection of the Helmholtz resonator against overheating caused by heat radiation from the combustion chamber through the flow channel towards the Helmholtz resonator volume could result. So it is from cooling technology View with the previous use of Helmholtz resonators required that a certain minimum throughput of cooling air flow through the Helmholtz resonator prevails. In the case of the atomization of liquid drops according to the invention within the Helmholtz resonator volume in front of the flow channel leading to the Combustion chamber leads, but is no additional air flow for cooling purposes required.
- a Helmholtz resonator volume that has at least one feed and discharge, can be introduced or removed from the liquid into the Helmholtz resonator volume this can be derived.
- a liquid into the interior of the Helmholtz resonator volume, it is possible for the flow volume or the Flow cross section for the one flowing through the Helmholtz resonator volume Supply air can be varied continuously and according to the currently prevailing acoustic conditions adapt.
- the Helmholtz resonator volume By filling the Helmholtz resonator volume with Liquid is the sound-absorbing behavior of the Helmholtz resonator in terms of to those arising within the flow area of the gas turbine system individually adjust disturbing oscillations.
- the fill the sound-absorbing resonator structure with liquid in such a way that the resonance frequency depending on the degree of filling of the resonator is just that Frequency of the oscillations due to the thermoacoustic vibrations corresponds.
- the operation of a Helmholtz resonator the is provided with the injection nozzle arrangement described above.
- the different resonance behavior of the resonator due to the mass flow the droplet and the degree of atomization are adjustable.
- Another advantageous aspect of filling the Helmholtz resonator volume connected to water affects the cooling of the resonator.
- Water is due to the prevailing temperature conditions due to the proximity of the combustion chamber, kept in the boiling state - typical Combustion pressures of 20 bar and temperatures around 250 ° C - so that for cooling purposes on an additional air supply within the resonator area can be dispensed with.
- a third, alternative solution to noise reduction within a turbomachine with a combustion chamber sees an injector assembly for the fuel within the flow channel that connects the Helmholtz resonator volume to the combustion chamber.
- the injector assembly atomizes fuel toward the combustion chamber.
- the fuel feed line faces in the fuel feed direction Injection nozzle arrangement also has a Helmholtz resonator volume the gaseous fuel supplied has a certain resonant natural frequency is imposed. Which is between the disturbing oscillation within the combustion chamber forming vibration and the vibration of the The phase oscillation which sets the fuel oscillation is to be selected such that at the so-called Rayleigh criterion for each operating state of the gas turbine system is not met.
- the Rayleigh criterion for fanning or damping thermoacoustic Vibrations is satisfied when the phase difference between reaction rate fluctuations and pressure fluctuations is less than ⁇ / 2.
- a fourth and last alternative solution for vibration damping or sound damping inside a turbomachine with a combustion chamber sees a Helmholtz resonator volume before, which is designed as a Fluidix switch.
- the "Helmholtz Resonator Fluidix switch” is connected to the fuel gas stream and at the same time with a connecting channel that opens directly into the combustion chamber.
- the Combination "Helmholtz resonator fluidix switch” has the task of the fuel mass flow in opposition to any combustion chamber vibration that may occur to modulate and thus dampen the vibration. So one can Vibration are always damped when the reaction, for example in Form of an increase in volume, increasing with decreasing pressure.
- Figure 1 shows a sound damping device for a turbomachine, for example Gas turbine plant with a combustion chamber 1, into which a flow channel 2 pre-compressed air is introduced with the addition of fuel.
- a turbomachine for example Gas turbine plant with a combustion chamber 1 into which a flow channel 2 pre-compressed air is introduced with the addition of fuel.
- the representation according to FIG. 1 shows a related one Fuel supply line does not open.
- thermoacoustic occur within the combustion chamber 1 Vibrations, which apply with the device shown in Figure 1 to dampen. So is in the flow direction in front of the flow channel 2 Helmholtz resonator volume 3 is provided, which has an air supply line 4.
- the Helmholtz resonator volume is capable 3 only a certain, limited damping effect to the thermoacoustic that is developing inside the combustion chamber 1 To exert vibrations, but it is only through the provision of an injector assembly 5 possible within the Helmholtz resonator volume 3, the Sound damping effect individually on those developing within the combustion chamber adapt thermoacoustic vibrations.
- the injector arrangement 5 which in front of the flow channel 2 in the flow direction in the Combustion chamber entering incoming air is arranged, preferably a liquid Water atomized into the finest drops of liquid, so that within the Flow channel 2 forms a liquid-air mixture 5 ', which preferably the entire flow channel 2 fills.
- the injection nozzle arrangement 5 is preferred arranged concentrically within the air supply line 4, so that sufficient a lot of supply air (see arrows) is introduced into the interior of the Helmholtz resonator 3 becomes.
- Liquid changes the prevailing within the liquid-gas mixture
- Speed of sound which has a targeted influence on the resonance behavior of the Helmholtz resonator volume 3 can be taken. With increasing The proportion of liquid in the liquid-gas mixture decreases the speed of sound significantly.
- the high variability of the is particularly advantageous due to a suitable choice of liquid droplet size and degree of atomization Influence on the resonance behavior of the Helmholtz resonator volume without the need to use a large volume of the Helmholtz resonator Training construction, as is the case with the prior art.
- the mass flow of the atomized liquid must be regulated individually.
- FIG. 2 shows a damping arrangement with a Helmholtz resonator volume 3 shown, which in addition to an air supply line 4 and the flow channel 2 towards Combustion chamber 1 has a water inlet or outlet channel 6 through which depending on the level within the Helmholtz resonator volume, add 3 water can be dissipated.
- a water inlet or outlet channel 6 through which depending on the level within the Helmholtz resonator volume, add 3 water can be dissipated.
- the total resonance behavior is within the Helmholtz resonator volume 3 of the Helmholtz resonator can be set individually, comparable to the arrangement described in Figure 1 by varying the mass flow through the injector assembly.
- stepless adjustable water level within the resonator volume 3 carries that in the resonator volume 3 water, which is at about 250 ° C and 20 bar prevailing pressure is in the boiling state, for cooling the resonator arrangement even at, so that additional cooling air supply can be dispensed with can.
- FIG. 3 shows a further alternative sound attenuation system for suppression represented by thermoacoustic vibrations within the combustion chamber 1.
- the Helmholtz resonator volume 3 is supplied with supply air via an air supply line 4, which are forwarded via a flow channel 2 in the direction of combustion chamber 1 becomes.
- the Helmholtz resonator volume 3 as well as partially Passing through flow channel 2, a fuel feed line 7 for gaseous Provided fuel that provides a nozzle outlet 8 at the outlet end by which a conical fuel cloud 9 emerges and into the interior of the combustion chamber 1 occurs.
- the Fuel supply line 7 also a Helmholtz resonator volume 10 before that a certain gaseous fuel flowing out of the nozzle outlet 8 Forces resonance frequency.
- thermoacoustic vibrations occur within the fuel chamber 1 in relation to the resonance frequency of the from the nozzle outlet 8 outflowing gaseous fuel.
- Helmholtz resonator volume 10 within the fuel supply line 7 can a certain phase difference between the fuel vibration and the thermoacoustic vibrations within the combustion chamber 1 set in this way be that the Rayleigh criterion for the stimulation of thermoacoustic vibrations is not met.
- FIG. 1 Another concept for sound absorption within a turbomachine a combustion chamber 1 is shown in FIG.
- Essential components of this Arrangement consist of a Helmholtz resonator volume 3 whose inner Volume size can be changed with a movable piston 11.
- a flip-flop damping channel 12 is provided within the volume 3.
- Such an arrangement is also known as "Helmholtz resonator fluidix switch” known.
- This arrangement is via an opening with the fuel feed line 7 connected in the same way via a connecting channel 13 is connected to the combustion chamber 1.
- the fuel feed line 7 opens into the shown Fall into the air supply line 4 through which the fuel supplied by the flow channel 2 is introduced into the combustion chamber 1.
- the idea behind the construction is the use of a "Fluidix switch", its vibration behavior due to the inside of the combustion chamber 1 forming thermoacoustic vibrations via the connecting channel 13 being affected.
- the aim is to match the resonance behavior of the Fluidix switch Frequency of the thermoacoustic vibrations within the combustion chamber 1 adapt.
- the adjustment can be done with the help of the movable piston 11 or as in the exemplary embodiment according to FIG. 2 with a corresponding one Degree of filling of the resonator volume 3 with a liquid.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP98810714.0A EP0974788B1 (fr) | 1998-07-23 | 1998-07-23 | Dispositif d'atténuation adaptée de bruit dans une turbomachine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP98810714.0A EP0974788B1 (fr) | 1998-07-23 | 1998-07-23 | Dispositif d'atténuation adaptée de bruit dans une turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0974788A1 true EP0974788A1 (fr) | 2000-01-26 |
EP0974788B1 EP0974788B1 (fr) | 2014-11-26 |
Family
ID=8236211
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98810714.0A Expired - Lifetime EP0974788B1 (fr) | 1998-07-23 | 1998-07-23 | Dispositif d'atténuation adaptée de bruit dans une turbomachine |
Country Status (1)
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EP (1) | EP0974788B1 (fr) |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1004823A3 (fr) * | 1998-11-10 | 2000-11-29 | Asea Brown Boveri AG | Dispositif d'amortissement pour la réduction de l'amplitude d'oscillation d'ondes acoustiques pour un brûleur |
US6634457B2 (en) * | 2000-05-26 | 2003-10-21 | Alstom (Switzerland) Ltd | Apparatus for damping acoustic vibrations in a combustor |
US6705428B2 (en) | 2000-12-08 | 2004-03-16 | Abb Turbo Systems Ag | Exhaust gas system with helmholtz resonator |
EP1557609A1 (fr) | 2004-01-21 | 2005-07-27 | Siemens Aktiengesellschaft | Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion |
EP1434006A3 (fr) * | 2002-12-23 | 2006-03-01 | Rolls-Royce Plc | Chambre de combustion pour turbine à gaz |
EP1762786A1 (fr) * | 2005-09-13 | 2007-03-14 | Siemens Aktiengesellschaft | Procédé et appareil pour réduire les vibrations thermo-accoustiques, en particulier dans une turbine |
EP2378199A1 (fr) | 2010-04-13 | 2011-10-19 | Siemens Aktiengesellschaft | Dispositif résonateur pour amortir la variation de pression dans une chambre de combustion et procédé d'opération d'un agencement de combustion |
EP2397761A1 (fr) * | 2010-06-16 | 2011-12-21 | Alstom Technology Ltd | Amortisseur de Helmholtz et procédé de régulation de la fréquence à résonance d'un amortisseur de Helmholtz |
EP2397759A1 (fr) * | 2010-06-16 | 2011-12-21 | Alstom Technology Ltd | Agencement d'amortisseur |
CN102356278A (zh) * | 2009-03-19 | 2012-02-15 | 西门子公司 | 燃气轮机燃烧*** |
EP2474784A1 (fr) | 2011-01-07 | 2012-07-11 | Siemens Aktiengesellschaft | Système de combustion pour turbine à gaz comprenant un résonateur |
CN103032898A (zh) * | 2012-12-31 | 2013-04-10 | 中国人民解放军国防科学技术大学 | 一种燃烧室混合增强装置 |
US8789372B2 (en) | 2009-07-08 | 2014-07-29 | General Electric Company | Injector with integrated resonator |
US8966903B2 (en) | 2011-08-17 | 2015-03-03 | General Electric Company | Combustor resonator with non-uniform resonator passages |
US9341375B2 (en) | 2011-07-22 | 2016-05-17 | General Electric Company | System for damping oscillations in a turbine combustor |
Citations (3)
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DE4305333C1 (de) * | 1993-02-20 | 1994-07-07 | Fasag Ag Suhr | Geräuschdämpfungsvorrichtung zur Reduktion von Mündungsgeräuschen bei Anlagen mit pulsierenden Gasströmungen |
US5431018A (en) * | 1992-07-03 | 1995-07-11 | Abb Research Ltd. | Secondary burner having a through-flow helmholtz resonator |
GB2288660A (en) * | 1994-04-23 | 1995-10-25 | Abb Management Ag | Apparatus for damping thermoacoustic vibrations in combustion chamber |
-
1998
- 1998-07-23 EP EP98810714.0A patent/EP0974788B1/fr not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US5431018A (en) * | 1992-07-03 | 1995-07-11 | Abb Research Ltd. | Secondary burner having a through-flow helmholtz resonator |
DE4305333C1 (de) * | 1993-02-20 | 1994-07-07 | Fasag Ag Suhr | Geräuschdämpfungsvorrichtung zur Reduktion von Mündungsgeräuschen bei Anlagen mit pulsierenden Gasströmungen |
GB2288660A (en) * | 1994-04-23 | 1995-10-25 | Abb Management Ag | Apparatus for damping thermoacoustic vibrations in combustion chamber |
Non-Patent Citations (1)
Title |
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ABOTT A. PUTNAM: "Combustion-Driven Oscillations in Industry", 1971, AMERICAN ELSEVIER, NEW YORK, XP002087281 * |
Cited By (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1004823A3 (fr) * | 1998-11-10 | 2000-11-29 | Asea Brown Boveri AG | Dispositif d'amortissement pour la réduction de l'amplitude d'oscillation d'ondes acoustiques pour un brûleur |
US6370879B1 (en) | 1998-11-10 | 2002-04-16 | Alstom | Damping device for reducing the vibration amplitude of acoustic waves for a burner |
US6634457B2 (en) * | 2000-05-26 | 2003-10-21 | Alstom (Switzerland) Ltd | Apparatus for damping acoustic vibrations in a combustor |
US6705428B2 (en) | 2000-12-08 | 2004-03-16 | Abb Turbo Systems Ag | Exhaust gas system with helmholtz resonator |
EP1434006A3 (fr) * | 2002-12-23 | 2006-03-01 | Rolls-Royce Plc | Chambre de combustion pour turbine à gaz |
EP1557609A1 (fr) | 2004-01-21 | 2005-07-27 | Siemens Aktiengesellschaft | Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion |
EP1762786A1 (fr) * | 2005-09-13 | 2007-03-14 | Siemens Aktiengesellschaft | Procédé et appareil pour réduire les vibrations thermo-accoustiques, en particulier dans une turbine |
WO2007031376A1 (fr) * | 2005-09-13 | 2007-03-22 | Siemens Aktiengesellschaft | Procede et dispositif pour l'amortissement d'oscillations thermo-acoustiques, notamment dans une turbine a gaz |
US8919128B2 (en) | 2005-09-13 | 2014-12-30 | Siemens Aktiengesellschaft | Method and device for damping thermoacoustic oscillations, in particular in a gas turbine |
CN101263343B (zh) * | 2005-09-13 | 2012-09-05 | 西门子公司 | 尤其在燃气轮机内阻尼热声振荡的方法和装置 |
CN102356278A (zh) * | 2009-03-19 | 2012-02-15 | 西门子公司 | 燃气轮机燃烧*** |
US8789372B2 (en) | 2009-07-08 | 2014-07-29 | General Electric Company | Injector with integrated resonator |
US9279586B2 (en) | 2010-04-13 | 2016-03-08 | Siemens Aktiengesellschaft | Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement |
EP2378199A1 (fr) | 2010-04-13 | 2011-10-19 | Siemens Aktiengesellschaft | Dispositif résonateur pour amortir la variation de pression dans une chambre de combustion et procédé d'opération d'un agencement de combustion |
WO2011128158A1 (fr) | 2010-04-13 | 2011-10-20 | Siemens Aktiengesellschaft | Dispositif de résonateur pour amortir l'oscillation de pression à l'intérieur d'une chambre de combustion et procédé pour faire fonctionner un agencement de combustion |
CN102822601A (zh) * | 2010-04-13 | 2012-12-12 | 西门子公司 | 衰减燃烧室内压力振荡的谐振装置和操作燃烧布置结构的方法 |
CN102822601B (zh) * | 2010-04-13 | 2014-11-12 | 西门子公司 | 衰减燃烧室内压力振荡的谐振装置和操作燃烧布置结构的方法 |
EP2397759A1 (fr) * | 2010-06-16 | 2011-12-21 | Alstom Technology Ltd | Agencement d'amortisseur |
EP2397761A1 (fr) * | 2010-06-16 | 2011-12-21 | Alstom Technology Ltd | Amortisseur de Helmholtz et procédé de régulation de la fréquence à résonance d'un amortisseur de Helmholtz |
US8727070B2 (en) | 2010-06-16 | 2014-05-20 | Alstom Technology Ltd | Helmholtz damper and method for regulating the resonance frequency of a Helmholtz damper |
US8869533B2 (en) | 2011-01-07 | 2014-10-28 | Siemens Aktiengesellschaft | Combustion system for a gas turbine comprising a resonator |
WO2012093011A1 (fr) | 2011-01-07 | 2012-07-12 | Siemens Aktiengesellschaft | Système de combustion pour turbine à gaz comprenant un résonateur |
EP2474784A1 (fr) | 2011-01-07 | 2012-07-11 | Siemens Aktiengesellschaft | Système de combustion pour turbine à gaz comprenant un résonateur |
US9341375B2 (en) | 2011-07-22 | 2016-05-17 | General Electric Company | System for damping oscillations in a turbine combustor |
US8966903B2 (en) | 2011-08-17 | 2015-03-03 | General Electric Company | Combustor resonator with non-uniform resonator passages |
CN103032898A (zh) * | 2012-12-31 | 2013-04-10 | 中国人民解放军国防科学技术大学 | 一种燃烧室混合增强装置 |
Also Published As
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