GB2288660A - Apparatus for damping thermoacoustic vibrations in combustion chamber - Google Patents
Apparatus for damping thermoacoustic vibrations in combustion chamber Download PDFInfo
- Publication number
- GB2288660A GB2288660A GB9506413A GB9506413A GB2288660A GB 2288660 A GB2288660 A GB 2288660A GB 9506413 A GB9506413 A GB 9506413A GB 9506413 A GB9506413 A GB 9506413A GB 2288660 A GB2288660 A GB 2288660A
- Authority
- GB
- United Kingdom
- Prior art keywords
- resonator
- connecting tube
- combustion chamber
- space
- resonator space
- 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.)
- Withdrawn
Links
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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Description
i
DESCRIPTION 2288660
APPARATUS FOR DAMPING THERMOACOUSTIC VIBRATIONS IN A COMBUSTION CHAMBER TECHNICAL FIELD
The present invention relates to the field of combustion technology. It relates to an apparatus f or damping thermoacoustic vibrations in a combustion cham- ber, in particular in the combustion chamber of a gas turbine, comprising a Helmholtz resonator having a resonator space and a connecting tube by means of which the resonator - space is connected to the combustion chamber.
Publication EP-Al-O 577 862, discloses such an apparatus.
PRIOR ART for example,
In combustion chambers, as used in particular in gas turbines, thermoacoustic vibrations are excited by an amplifying interaction between thermal and acoustic disturbances. Undesirably high vibration amplitudes can appear in the process if acoustic natural vibrations of the combustion chamber are excited. The adverse consequences are inadmissably high mechanical loading of the combustion chamber, a rise in the emissions through inhomogeneous -combustion and, in the extreme case. extinguishing of the flame. This problem is intensified in modern combustion chambers, since cooling-air openings in the combustion chamber which would dampen the pressure pulsations are as far as possible dispensed with.
In gas-turbine combustion chamberst depending on the size of the combustion chamber, a narrow-band excitation of high amplitude in the frequency range of 100 to 250 Hz typically occurs. This excitation can be dampened by means of so-called Helmholtz resonators,, the frequency of the Helmholtz resonator having to be accurately coordinated with the frequency of. the combustion-chamber vibration. In connection with an afterburner for a gas turbine, it has already been proposed in the publication mentioned at the beginning to use such a Helmholtz resonator for this purpose.
But experience now shows that, depending on the operating conditions (full load/partial load, ambient temperature. fuel/air ratio, gas or oil operation.. etc.),, the combustion-chamber frequency can vary by up to 20%. On the other hand, the frequency in the Helmholtz resonator is also dependent upon the operating conditions: experimental tests have shown that the Belmholtz frequency can be displaced during rising pulsation amplitudes by up to 19% towards lower values. But it is known that the damping performance is massively reduced by only slight differences between the two frequencies.
SUMMARY OF THE INVENTION
The object of the invention, then, is to specify a damping apparatus having a Helmholtz resonator, by means of which damping apparatus a uniform damping performan e can be achieved even under fluctuating operating conditions.
This object is achieved in an apparatus of the type mentioned at the beginning when the Helmholtz resonator is equipped with first means for controlling the resonator frequency as a function of the frequency of the combustion-chamber vibrations.
The essence of the invention therefore consists in designing the apparatus in such a way that the resonator frequency is appropriately readjusted during a change in the frequency of the vibration to be dampened.
The readjustment of the resonator can be effected in different ways. In a first preferred embodiment of the apparatus according to the invention, the first means comprise second means for controlling the density of the gases located in the connecting tube. This enables the frequency of the resonator to be changed in a simple manner without a (mechanically complicated) change in the resonator volume The control can be realized in an especially simple manner when, in a second preferred embodiment, the second means control the density of the gases located in the connecting tube by changing the temperature.
A first advantageous embodiment of the temperature control is characterized in that the second means comprise an electric heating element by which the gases located in the resonator space can be heated.
A second advantageous embodiment of the temperature control is distinguished by the fact that the second means comprise an electric heating element by which the gases located in the connecting tube can be heated.
A third advantageous embodiment of the temperature control is characterized in that the second means comprise a scavenging-air feed line which leads.
into the resonator space and by means of which scavenging air can be directed through the resonator space. The temperature in the resonator space can be specifically lowered relative to the combustion chamber by the (relatively cold) scavenging air in order to stabilize frequency differences.
A further embodiment of the apparatus according to the invention is distinguished by the fact that the second means comprise a gas feed line which leads into the resonator space and by means of which gases of different density can be directed alternatively into the resonator space. In this way, the resonance frequency can be changed by changing the average density in a gas mixture of different composition.
Further embodiments follow from the dependent claims.
BRIEF DESCRIPTION OF THE FIGURES The invention is to be described in more detail below with reference to exemplary embodiments in connection with the drawing, in which:
Fig. 1 shows in schematic representation afirst exemplary embodiment of an apparatus accor ding to the invention having a heatable resonator space; Fig. 2 shows in schematic representation a second exemplary embodiment of an apparatus accor ding to the invention having a heatable connecting tube; shows in schematic representation a third exemplary embodiment of an apparatus accor ding to the invention having a, device for feeding auxiliary gases of a different density; shows in schematic representation a fourth exemplary embodiment of an apparatus accor ding to the invention having a device for feeding scavenging air; and.
shows in schematic representation apparatus according to Fig. 1 in combination with a complete control system is Fig. 3 Fig. 4 Fig. 5 0.
1 The essence of the invention is to provide a Helmholtz resonator which can be controlled with simple means and the frequency of which can be accurately regulated to the combiustion-chamber vibration frequency in all operating states. The frequency of the Helmholtz resonator is described by the following generalized ecuation:
S, 0 =Cl, M-WplIV where: Helmholtz-resonator frequency ell_ - sound velocity in the resonator = crosssectional area of the connecting tube 41 1 = length of the connecting tube pjjj = air density in the connecting tube v = resonator volume p,, = air density in the resonator The Helmholtz frequency w can now be - detuned in various ways in accordance with the combustionchamber frequency. A first exemplary embodiment for an apparatus having controllable resonator frequency is schematically shown in Fig. 1. A Helmholtz resonator 1 is shown which comprises a resonator space 2 enclosed by a resonator wall 13 and having the resonator volume V. The resonator space 2 is connected via a connecting tube 3 (length 1; cross-sectional area s; see Fig. 3) to a combustion chamber 7 which in turn is defined by a combustion-chamber wall 8.
The detuning of the resonator is effected here by increasing the temperature in the resonator space 2 by means of a controlled (electric) heating element 5 which is either attached directly in the gas volume or heats up the gas volume via the resonator wall 13. An increase in the temperature by 10% from, for example. 6000K to 660K reduces the density pIII by 10% and thus (according to the abovementioned formula) increases the resonator frequency by 5%.
It is advantageous in this case to insulate thermally at least the resonator space 2 by means of thermal insulation 4. Furthermore, it is advantageous to blow shielding air 9 from outside (e.g. f rom the plenum 10 of a gas turbine) into the connecting tube 3 to prevent the ingress of hot gases from the combustion chamber 7 into the resonator space 2. The requisite heating output which has to be applied to the terminals 6a,b of the heating element 5 can thereby be reduced to a minimum.
A second possibility of detuning the resonator by temperature change is shown in the exemplary embodiment in Fig. 2. Here, the gas in the connecting tube 3 to the combustion chamber 7 is heated with a heating element 12 and thus the gas density is k A --- reduced directly in the connecting tube 3. The heating element 12 can be, for example, a heater winding wound around the connecting tube 3. Here, tooi the requisite heating output can be minimized by the connecting tube 3 being surrounded in a primary manner with thermal insulation 11 and by the resonator space 2 also being surrounded in a secondary manner with thermal insulation 4. The feeding of shielding air 9 can also be provided as in Fig. 1.
A third possibility of detuning the resonator by temperature change is reproduced in the exemplary embodiment in Fig. 4. Via a scavenging-air feed line 26 equipped with a control valve 19. (cool) scavenging air is sent here in a controlled manner through the Belmholtz resonator 1 and thus the temperature in the resonator is influenced. At a small scavenging-air quantity,, the air is heated in the resonator space 2 from the hot-gas side (i.e. from the combustion chamber 7). At a high scavenging-air quantity, the air in the resonator space 2 cools down accordingly. It is also advantageous in this case if the Belmholtz resonator 1 together with connecting tube 3 is surrounded with thermal insulation 4 and 11 respectively. The air in the resonator space 2 can thereby be heated to a higher temperature if this is necessary. Furthermore,, it is advantageous if the connecting tube -3 projects with a tube piece 20 slightly into the combustion chamber 7 so that the thermal coupling of the resonator to the combustion chamber 7 is improved. Thit assists the heating of the air in the resonator space.
A further possibility of detuning the resonator is shown in the exemplary embodiment in Fig. 3. The frequency is detuned here by adding a gas of higher density (e.g. C02) or lower density (e.g. helium) into the resonator space 2. Here. too,, the sound velocity is varied via a density change; but the density change is not based on the temperature change in a gas but on the change in the mixture ratio of gases of various density. For this purpose, at least - 7 one gas feed line 14 is attached to the resonator space 2, through which gas f eed line 14 the auxiliary gases can be f ed. If two branches 15, 16 having one control valve 17, 18 each are provided at the gas feed line 14,' via which branches 15, 16 a gas of higher and lower density can be added simultaneously in a controlled manner, frequency changes at the resonator in both directions can easily be achieved.
The phase angle (the phase difference) 10 between the pressure vibration in the combustion chamber 7 and that in the resonator space 2 is the most suitable control variable for the frequency control. in which case:
= -900 for fBY, = fRE < -900 for fBY,. > fRE > -900 for fBY, < fRE where fBK = combustion-chamber frequency, fRE = resona tor frequency, and = phase angle.
The phase angle reacts very sensitively to frequency differences and is therefore the most suitable control variable for the heating output or scavenging-air or auxiliary-gas supply. A corresponding complete control system for an arrangement from Fig. 1 is reproduced in Fig. 5. To record the pressure vibrations, in' each case at least one pressure sensor 21a and 21b respectively is arranged at a suitable point in the combustion chamber 7 and in the resonator space 2. The measuring signals from the pressure sensors 21a,b are processed in downstream measuring transducers 22, 23 and transmitted to the two inputs of a phase comparator 24 which derives a control signal from the phase difference and delivers it to a following activating unit 25. The activating unit 25 contains a power part which controls the heating output in the heating element 5. In the examples from Figs. 2 to 4, the heating element 12 and the control valves 17 to 19 respectively are accordingly connected to. the activating unit 25.
h Aw- The invention results overall in a simple and functionally reliable apparatus for damping the thermoacoustic vibrations in combustion chambers even under fluctuating operating conditions.
Claims (1)
- PATENT CLAIMS1. Apparatus for damping thermoacoustic vibrations in a combustion chamber in particular in the combustion chamber of a gas turbine, comprising a Belmholtz resonator having a resonator space and a connecting tube by means of which the resonator space is connected to thecombustion chamber characterized in that the Helmholtz resonator is equipped with first means for controlling the resonator frequency as a function of the frequency of the combustion-chamber vibrations.2. Apparatus according to Claim 1, characterized in that the first means comprise second means for controlling the density of the gases located in the connecting tube 0 3. Apparatus according to Claim 2# characterized in that the second means control the density of the gases located in the connecting tube by changing the temperature.4. Apparatus according to Claim 3,, characterized in that the second means comprise an electric heating element by which the gases located in the rdsonator space can be heated.5. Apparatus according to Claim 3, characterized in that the second means comprise a scavenging-air feed line which leads into the resonator space and by means of which scavenging air can be directed through the resonator space 0 6. Apparatus a6cording to Claim 5. characterized in that a control valve is provided for controlling the scavenging-air feed in the scavenging air feed line.Apparatui according to either of Claims 5 or 6, characterized in that, to improve the thermal coupling of the resonator space to the combustion chamber the connecting tube projects with a tube piece into the combustion chamber h Apparatus according to Claim 3. characterized in that the second means comprise an electric heating element by which the gases located in the connecting tube can be heated.9. Apparatus according to one of Claims. 3 to 8, characterized in that the resonator space and/or the connecting tube is surrounded x,ith thermal insulation -- 0 1.0. Apparatus according to Claim 2, characterized in that the second means comprise a gas feed line which leads into the resonator space and by means of which gases of different density can be directed alternatively into the resonator space 11. Apparatus according to either of Claims 4 and 8, characterized in that,, to prevent the ingress of hot gases from the combustion chamber into the resonator space shielding air is. blown from outside into the connecting tube 12. Apparatus according to Claim 2, characterized 20 in that the first means comprise a control circuit which controls the density of the gases located in the connecting tube. - in accordance with the phase difference between the combustion-chamber vibrations and the resonator vibrations.13. Apparatus according to Claim 12, characterized in that the control circuit comprises at least. one pressure sensor each in the combustion chamber and the resonator space downstream measuring transducers comparator -, and ah activating unit it 01 a phase 0 11.14. Apparatus for damping thermoacoustic vibrations in a combustion chamber substantially as herein described with reference to any of figures 1 to 4 of the accompanying drawings.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE4414232A DE4414232A1 (en) | 1994-04-23 | 1994-04-23 | Device for damping thermoacoustic vibrations in a combustion chamber |
Publications (2)
Publication Number | Publication Date |
---|---|
GB9506413D0 GB9506413D0 (en) | 1995-05-17 |
GB2288660A true GB2288660A (en) | 1995-10-25 |
Family
ID=6516264
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB9506413A Withdrawn GB2288660A (en) | 1994-04-23 | 1995-03-29 | Apparatus for damping thermoacoustic vibrations in combustion chamber |
Country Status (3)
Country | Link |
---|---|
JP (1) | JPH07293885A (en) |
DE (1) | DE4414232A1 (en) |
GB (1) | GB2288660A (en) |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0974788A1 (en) * | 1998-07-23 | 2000-01-26 | Asea Brown Boveri AG | Device for directed noise attenuation in a turbomachine |
WO2004051063A1 (en) * | 2002-12-02 | 2004-06-17 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor, and gas turbine with the combustor |
GB2396687A (en) * | 2002-12-23 | 2004-06-30 | Rolls Royce Plc | Helmholtz resonator for combustion chamber use |
EP1517087A1 (en) * | 2003-09-16 | 2005-03-23 | General Electric Company | Method and apparatus to decrease combustor acoustics |
EP1669670A1 (en) * | 2004-12-11 | 2006-06-14 | ROLLS-ROYCE plc | Combustion chamber for a gas turbine engine |
EP1724527A1 (en) * | 2005-05-13 | 2006-11-22 | Siemens Aktiengesellschaft | Combustion chamber and method of suppressing combustion vibrations |
EP1775515A2 (en) * | 2005-10-14 | 2007-04-18 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Resonating device for combustion chamber, combustion chamber and method for adjusting the acoustic characteristics of a combustion chamber |
US20090293481A1 (en) * | 2005-09-13 | 2009-12-03 | Sven Bethke | Method and Device for Damping Thermoacoustic Oscillations, in Particular in a Gas Turbine |
US7661267B2 (en) | 2003-12-16 | 2010-02-16 | Ansaldo Energia S.P.A. | System for damping thermo-acoustic instability in a combustor device for a gas turbine |
US7857094B2 (en) | 2006-06-01 | 2010-12-28 | Rolls-Royce Plc | Combustion chamber for a gas turbine engine |
EP2302302A1 (en) * | 2009-09-23 | 2011-03-30 | Siemens Aktiengesellschaft | Helmholtz resonator for a gas turbine combustion chamber |
EP2378199A1 (en) | 2010-04-13 | 2011-10-19 | Siemens Aktiengesellschaft | Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement |
US9169804B2 (en) | 2013-07-18 | 2015-10-27 | Rolls-Royce Plc | Duct and method for damping pressure waves caused by thermoacoustic instability |
EP3418637A1 (en) * | 2017-06-20 | 2018-12-26 | General Electric Technology GmbH | Variable frequency helmholtz dampers |
EP3434876A1 (en) * | 2017-07-25 | 2019-01-30 | Siemens Aktiengesellschaft | Combustor apparatus and method of operating combustor apparatus |
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DE19851636A1 (en) * | 1998-11-10 | 2000-05-11 | Asea Brown Boveri | Damping device for reducing vibration amplitude of acoustic waves for burner for internal combustion engine operation is preferably for driving gas turbo-group, with mixture area for air and fuel |
DE10002984C1 (en) * | 2000-01-24 | 2001-08-09 | Daimler Chrysler Ag | Acoustic absorber and method for sound absorption |
DE10026121A1 (en) * | 2000-05-26 | 2001-11-29 | Alstom Power Nv | Device for damping acoustic vibrations in a combustion chamber |
DE50110932D1 (en) | 2000-12-08 | 2006-10-19 | Alstom Technology Ltd | Exhaust system with Helmholtz resonator |
EP1557609B1 (en) | 2004-01-21 | 2016-03-16 | Siemens Aktiengesellschaft | Device and method for damping thermoacoustic oscillations in a combustion chamber |
DE102004015186A1 (en) * | 2004-03-29 | 2005-10-20 | Alstom Technology Ltd Baden | Gas turbine combustor and associated operating method |
EP1624251B1 (en) * | 2004-08-03 | 2012-02-29 | Siemens Aktiengesellschaft | Apparatus for reducing thermoacoustic oscillations in combustion chambers with adjustable resonance frequency |
DE102005035085B4 (en) * | 2005-07-20 | 2014-01-16 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method for adjusting the acoustic properties of a combustion chamber |
KR100905254B1 (en) * | 2007-11-06 | 2009-06-29 | 홍정구 | Apparatus and method for the decrease of the operating region of combustion instability in a combustor |
JP2008101910A (en) * | 2008-01-16 | 2008-05-01 | Doshisha | Thermoacoustic device |
CH699322A1 (en) * | 2008-08-14 | 2010-02-15 | Alstom Technology Ltd | METHOD FOR SETTING A Helmholtz resonator AND HELMHOLTZ RESONATOR FOR IMPLEMENTING THE PROCESS. |
US8789372B2 (en) | 2009-07-08 | 2014-07-29 | General Electric Company | Injector with integrated resonator |
RU2508506C2 (en) * | 2009-09-01 | 2014-02-27 | Дженерал Электрик Компани | Method and unit for fluid feed in gas turbine engine combustion chamber |
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 |
EP2623732A1 (en) * | 2012-02-02 | 2013-08-07 | Siemens Aktiengesellschaft | Assembly and method for dampening acoustic vibrations in such an assembly |
JP5959870B2 (en) * | 2012-02-15 | 2016-08-02 | 三菱重工業株式会社 | Acoustic damper, combustor, gas turbine |
EP2831504B1 (en) * | 2012-03-30 | 2018-12-26 | Ansaldo Energia IP UK Limited | Combustion chamber seal segments equipped with damping devices |
CN114811650B (en) * | 2022-06-01 | 2023-02-07 | 清华大学 | Electric heating stable combustion device and method and storage medium |
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WO1993010401A1 (en) * | 1991-11-15 | 1993-05-27 | Siemens Aktiengesellschaft | Arrangement for suppressing combustion-caused vibrations in the combustion chamber of a gas turbine system |
Cited By (35)
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---|---|---|---|---|
EP0974788A1 (en) * | 1998-07-23 | 2000-01-26 | Asea Brown Boveri AG | Device for directed noise attenuation in a turbomachine |
WO2004051063A1 (en) * | 2002-12-02 | 2004-06-17 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor, and gas turbine with the combustor |
US7832211B2 (en) | 2002-12-02 | 2010-11-16 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor and a gas turbine equipped therewith |
US7076956B2 (en) * | 2002-12-23 | 2006-07-18 | Rolls-Royce Plc | Combustion chamber for gas turbine engine |
GB2396687A (en) * | 2002-12-23 | 2004-06-30 | Rolls Royce Plc | Helmholtz resonator for combustion chamber use |
EP1434006A3 (en) * | 2002-12-23 | 2006-03-01 | Rolls-Royce Plc | Combustion chamber for gas turbine engine |
EP1517087A1 (en) * | 2003-09-16 | 2005-03-23 | General Electric Company | Method and apparatus to decrease combustor acoustics |
US7272931B2 (en) | 2003-09-16 | 2007-09-25 | General Electric Company | Method and apparatus to decrease combustor acoustics |
US7661267B2 (en) | 2003-12-16 | 2010-02-16 | Ansaldo Energia S.P.A. | System for damping thermo-acoustic instability in a combustor device for a gas turbine |
US7448215B2 (en) | 2004-12-11 | 2008-11-11 | Rolls-Royce Plc | Combustion chamber for a gas turbine engine |
EP1669670A1 (en) * | 2004-12-11 | 2006-06-14 | ROLLS-ROYCE plc | Combustion chamber for a gas turbine engine |
EP1724527A1 (en) * | 2005-05-13 | 2006-11-22 | Siemens Aktiengesellschaft | Combustion chamber and method of suppressing combustion vibrations |
US8919128B2 (en) * | 2005-09-13 | 2014-12-30 | Siemens Aktiengesellschaft | Method and device for damping thermoacoustic oscillations, in particular in a gas turbine |
US20090293481A1 (en) * | 2005-09-13 | 2009-12-03 | Sven Bethke | Method and Device for Damping Thermoacoustic Oscillations, in Particular in a Gas Turbine |
EP1775515A3 (en) * | 2005-10-14 | 2014-10-22 | Deutsches Zentrum für Luft- und Raumfahrt e. V. | Resonating device for combustion chamber, combustion chamber and method for adjusting the acoustic characteristics of a combustion chamber |
EP1775515A2 (en) * | 2005-10-14 | 2007-04-18 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Resonating device for combustion chamber, combustion chamber and method for adjusting the acoustic characteristics of a combustion chamber |
US7857094B2 (en) | 2006-06-01 | 2010-12-28 | Rolls-Royce Plc | Combustion chamber for a gas turbine engine |
US8689933B2 (en) * | 2009-09-23 | 2014-04-08 | Siemens Aktiengesellschaft | Helmholtz resonator for a gas turbine combustion chamber |
WO2011036073A1 (en) * | 2009-09-23 | 2011-03-31 | Siemens Aktiengesellschaft | Helmholtz resonator for a gas turbine combustion chamber |
EP2302302A1 (en) * | 2009-09-23 | 2011-03-30 | Siemens Aktiengesellschaft | Helmholtz resonator for a gas turbine combustion chamber |
US20120228050A1 (en) * | 2009-09-23 | 2012-09-13 | Ghenadie Bulat | Helmholtz resonator for a gas turbine combustion chamber |
RU2511939C2 (en) * | 2009-09-23 | 2014-04-10 | Сименс Акциенгезелльшафт | Helmholtz resonator for combustion chamber of gas turbine |
CN102822601B (en) * | 2010-04-13 | 2014-11-12 | 西门子公司 | Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement |
US20130025282A1 (en) * | 2010-04-13 | 2013-01-31 | Ghenadie Bulat | Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement |
CN102822601A (en) * | 2010-04-13 | 2012-12-12 | 西门子公司 | Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement |
WO2011128158A1 (en) | 2010-04-13 | 2011-10-20 | Siemens Aktiengesellschaft | Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement |
EP2378199A1 (en) | 2010-04-13 | 2011-10-19 | Siemens Aktiengesellschaft | Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement |
RU2569786C2 (en) * | 2010-04-13 | 2015-11-27 | Сименс Акциенгезелльшафт | Resonator for pressure oscillations damping in combustion chamber and method for combustion system control |
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 |
US9169804B2 (en) | 2013-07-18 | 2015-10-27 | Rolls-Royce Plc | Duct and method for damping pressure waves caused by thermoacoustic instability |
EP3418637A1 (en) * | 2017-06-20 | 2018-12-26 | General Electric Technology GmbH | Variable frequency helmholtz dampers |
US11230974B2 (en) | 2017-06-20 | 2022-01-25 | General Electric Company | Variable frequency Helmholtz dampers |
EP3434876A1 (en) * | 2017-07-25 | 2019-01-30 | Siemens Aktiengesellschaft | Combustor apparatus and method of operating combustor apparatus |
WO2019020474A1 (en) * | 2017-07-25 | 2019-01-31 | Siemens Aktiengesellschaft | Combustor apparatus and method of operating combustor apparatus |
US11525396B2 (en) | 2017-07-25 | 2022-12-13 | Siemens Energy Global GmbH & Co. KG | Combustor apparatus with bleed arrangement and resonator with cooling flow and method of operating combustor apparatus |
Also Published As
Publication number | Publication date |
---|---|
GB9506413D0 (en) | 1995-05-17 |
JPH07293885A (en) | 1995-11-10 |
DE4414232A1 (en) | 1995-10-26 |
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