EP1557609A1 - Vorrichtung und Verfahren zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer - Google Patents
Vorrichtung und Verfahren zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer Download PDFInfo
- Publication number
- EP1557609A1 EP1557609A1 EP04001240A EP04001240A EP1557609A1 EP 1557609 A1 EP1557609 A1 EP 1557609A1 EP 04001240 A EP04001240 A EP 04001240A EP 04001240 A EP04001240 A EP 04001240A EP 1557609 A1 EP1557609 A1 EP 1557609A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- resonator
- volume
- cooling air
- 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
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Classifications
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00013—Reducing thermo-acoustic vibrations by active means
Definitions
- the present invention relates to the field combustion chambers, particularly gas turbine combustion chambers.
- the invention comprises a device and method for reducing thermoacoustic oscillations in gas turbine combustion chambers.
- the invention relates more specifically to a Helmholtz resonator, which has a resonating volume in connection with the combustion chamber volume.
- Thermoacoustic oscillations occur in combustion chambers due to the interference between thermal and acoustic fluctuations. Such combustion chamber instabilities can result in acoustic pressure oscillations with high amplitudes (more than 160 dB) and at low frequencies (hundreds of Hertz in gas turbines). Such oscillations might also increase pollutant formation (i.e NOx) due to inhomogeneous temperature distributions inside the combustion chamber. Furthermore, oscillations of this nature give rise to severe mechanical stresses, which cause damage and reduce the life span of the combustion chamber.
- Helmholtz resonators have often been employed as a means of damping such thermoacoustic oscillations in combustion chambers.
- a Helmholtz resonator consists of a hollow air space which communicates with a volume of air outside the resonator volume via an elongated connective opening.
- An air plug present in the connective opening forms the mass that resonates by being driven by the spring force formed by the air enclosed in the hollow resonator air space.
- the resonant frequency of the Helmholtz resonator depends on the cross-sectional area of the connective opening (S), on the volume (V) of the hollow air space and on the length (L) of the air plug formed in the connective opening.
- Helmholtz resonators When Helmholtz resonators are driven by acoustic energy at the resonant frequency, the resonators will absorb a maximum amount of incoming acoustic energy. However, because they are tuned systems, the absorption decreases rapidly as the frequency of the incoming acoustic energy varies substantially from the resonant frequency. Therefore, the principle limitation of Helmholtz resonators is that they attenuate sound energy efficiently only within a narrow frequency range centred at their tuned resonant frequency.
- US 2002/0000343 A1 discloses a Helmholtz resonator containing a closed air space connected to a gas turbine combustion chamber.
- the disclosed apparatus is provided with a hollow body, the volume of which can be changed by adding or draining a fluid via a supply line, and which is arranged either within the Helmholtz resonator volume or adjacent to it in such a way that the resonance volume of the Helmholtz resonator changes when the volume of the hollow body changes.
- EP 0 974 788 A1 teaches a Helmholtz resonator in connection with a combustion chamber.
- An injection nozzle is located within the resonating volume of the Helmholtz resonator and is directed towards the mouth of the opening connecting the resonating volume to the combustion chamber.
- a fine fluid spray is introduced into the connective opening, which effects the mass of the air plug within the connecting opening and therefore effects the resonance behaviour of the entire system.
- DE 100 04 991 A1 discloses a Helmholtz resonator in connection with a motor engine via a long pipe in which at least two holes are located, which are at a distance from each other along the pipe. The two holes have covers which allow the cross-sections of the holes to be varied, which effects the resonance behaviour of the Helmholtz system.
- the present invention describes an apparatus and method for damping thermoacoustic oscillations as well as a combustor arrangement comprising this apparatus that enables continuous adaptation to frequencies of the vibrations to be damped even under the high pressure conditions which occur in gas turbines.
- the device comprises a Helmholtz resonator, which consists of a hollow resonating volume which is in connection with a combustion chamber via a connective opening.
- the device has the unique characteristic that an adjustable flow of cooling air can be introduced into the resonating volume and connective opening. This is realised according to the invention by suitable means for adjusting a flow of cooling air into the resonator volume.
- the present invention allows for the first time the resonance frequency of the Helmholtz resonator to be adjusted by a dynamic flow of cooling air.
- the device of the present invention allows cooling air flow to be introduced into the resonator volume through at least one opening located on the resonator.
- a preferred embodiment of the invention allows the cross-sectional area of said opening to be adjusted so as to control the amount of cooling air flowing into the resonator volume.
- a preferred embodiment of the device of the present invention comprises the introduction of cooling air into the resonator volume via several openings located on the resonator itself.
- the cross-sections of the openings are adjustable. In this way the openings can be completely closed, which therefore reduces the number of effective openings in the resonator.
- the closing of the openings could for instance be achieved by having a Helmholtz resonator with a double wall structure, both walls having aligned openings. One of the walls could then be turned in order to alter the alignment of the through bores forming the openings in the walls. The openings could then be closed.
- the number of openings in the resonator has been found to effect the resonating properties of the Helmholtz resonator.
- a homogeneous distribution of the number of openings advantageously effects the maximum airflow as well as the tuning sensitivity.
- the supplied cooling air provides a double function of blocking hot gas from the combustion chamber entering the Helmholtz resonator, as well as achieving the desired tuning.
- the interval of change in the mass flow is sufficiently small for a broad tuning range without reducing the cooling air mass flow below a limit for secure cooling or exceeding an acceptable amount of cooling air.
- a further preferred embodiment of the device involves the supply of air to the resonator volume via an inlet pipe, the cross-sectional area of which can narrowed.
- This might be a choke-like mechanism or a valve or the like. The amount and pressure of the cooling air entering the resonator volume can thus be controlled.
- Another preferred embodiment comprises a gas turbine combustion chamber incorporating the device of the present invention.
- Gas turbines are characterised by the release of large amounts of energy. Therefore, combustion instabilities could have particularly severe consequences. In particular heavy duty gas turbines such as those with a power production rate of more than 50 MW can suffer from such instabilities. Additionally, with such energy output rates cooling of the combustion chamber is of particular importance, therefore the cooling air supplied to the Helmholtz resonator provides a double function of blocking hot gas from the combustion chamber as well as achieving the desired tuning effect.
- the present invention describes a method which comprises a Helmholtz resonator, which consists of a hollow resonating volume which is in connection with a combustion chamber via a connective opening.
- the method comprises an adjustable flow of cooling air to be introduced into the resonating volume and connective opening.
- the method of the present invention allows for the first time the resonance frequency of the Helmholtz resonator to be adjusted by a dynamic flow of cooling air.
- the method comprises the detection of combustion instabilities so as to instantaneously adapt the mass flow of cooling air and therefore suppress the instability by dynamically adjusting the frequency of the Helmholtz resonator accordingly. This can viewed as an active instability control.
- FIG. 1 shows a gas turbine 1 comprising a compressor 6, a combustion chamber 10 and turbine.
- air (arrow 2) enters the compressor 6, is compressed, and then compressed air 3 passes along conduit 7 into combustion chamber 10.
- Fuel (arrow 4) is introduced into the combustion chamber via an inlet (not shown) where it is mixed with the compressed air and the mixture burned.
- the resulting combustion gases (arrow 5) then pass along discharge line 8 into the turbine 9.
- Thermoacoustic oscillations originate in the burner located inside the combustion chamber, and are particularly likely to occur in low NOx emission premix burners.
- thermoacoustic oscillations produce fluctuations in heat release, for instance by perturbing the fuel-air ratio or flame shape. Such combustion instabilities can in turn generate more thermoacoustic oscillations which are reflected by the combustion chamber 10 inner walls and can then result in self-sustaining oscillations.
- a Helmholtz resonator 11 is arranged on the surface of the combustion chamber 10. The hollow volume of the Helmholtz resonator is in connection with the inner volume of the combustion chamber 10 via an elongated connective opening 15.
- FIG. 2 schematically shows the preferred configuration of the Helmholtz resonator 11 of the present invention.
- the hollow volume 23 of the Helmholtz resonator 11 is in connection with the inner volume 24 of the combustion chamber 10 via an elongated connective opening 15.
- Equally spaced openings or holes 12 are arranged on the surface of the Helmholtz resonator 11. Cooling air flow 14, supplied from the compressor 6, is introduced into the hollow volume 23 of the Helmholtz resonator 11 via openings 12.
- the cross-sectional area of the openings 12 can be adjusted by covering the openings 12 with a cover mechanism 13. A variety of methods of covering the openings 12 or holes would be available to a person skilled in the art.
- the present invention allows, for the first time, the resonance frequency of the Helmholtz resonator 11 to be adjusted by a dynamic flow 14 of cooling air. Furthermore.
- the use of cooling air 14 provides a double function of blocking hot gas from the combustion chamber 10 entering the Helmholtz resonator 11, as well as achieving the desired tuning of the resonance frequency.
- Figure 3 shows a preferred embodiment of the invention illustrating how the variable cross-sectional area of the openings 12 might be achieved.
- Figure 3 shows a cut-away section of the Helmholtz resonator 11 of the present invention having a double wall structure with outer wall 16 and inner wall 17.
- Outer wall 16 has one or more homogeneously spaced openings 12A on its surface, while inner wall 17 also has one or more homogeneously spaced openings 12B on its surface. Openings 12A and 12B are aligned with each other.
- Outer wall 16 or inner wall 17 can be turned. In this way the alignment of the openings 12A and 12B would then be altered and the cross-section of the openings 12A,12B would be changed or the openings 12A,12B could be completely closed.
- the number of openings 12A,12B in the resonator 11 has been found to effect the resonating properties of the Helmholtz resonator 11.
- the number of openings 12A,12B advantageously effects the maximum air flow 14 through the resonator 11 as well as the tuning sensitivity.
- Figure 3 also schematically depicts a possible arrangement for the active stability control mechanism as a closed loop process.
- a sensor 36 is in connection with the combustion chamber 10.
- the sensor 36 would advantageously detect changes in pressure inside the combustion chamber 10 (not shown).
- the sensor 36 is connected to a control unit 34, which is in turn connected to an electric motor 32.
- the electric motor 32 When a pressure difference is detected, the electric motor 32 will turn a shaft 30, which is connected to wall 16 or 17 of the Helmholtz resonator 11, where said wall can be rotated around the axis of the shaft 30.
- the openings 12A,12B in the Helmholtz resonator 11 will be opened or closed in such a way as to adapt the resonant frequency of the Helmholtz resonator 11 and thus damp the thermoacoustic oscillations appearing in the combustion chamber 10 (see fig. 2).
- the motor 32 By having numerous openings 12A,12B in the Helmholtz resonator 11, the motor 32 must only turn the shaft 30 through a small angle for there to be a significant change in the effective cross-section of the openings 12A,12B, therefore the system can react quickly and efficiently to adapt the resonant frequency of the Helmholtz resonator 11 and therefore damp the oscillations appearing in the combustion chamber 10.
- FIG 4 also shows a preferred embodiment of the invention having a valve mechanism 18 which enables the pressure and the amount of cooling air flow 20 flowing into the openings 12 in the Helmholtz resonator 11, to be directly controlled.
- the mechanism depicted by 18 could also be a choke-like mechanism.
- the cooling air flow 20 passes along a pipe 19 in which the air encounters the choke mechanism or valve, the air then passes into a cavity 21 which contains the Helmholtz resonator 11.
- the cavity 21 occurs between an outer wall 22 and the wall of the Helmholtz resonator 11.
- the valve 18 could also be connected to a closed loop active stability control mechanism, whereby a pressure sensor 36 would detect changes in the combustion chamber 10 and relay the detection data to a control unit 34 which in turn could suitably adapt the valve position so as to change the pressure and amount of the airflow 20 passing through the openings 12.
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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)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04001240.3A EP1557609B1 (de) | 2004-01-21 | 2004-01-21 | Vorrichtung und Verfahren zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04001240.3A EP1557609B1 (de) | 2004-01-21 | 2004-01-21 | Vorrichtung und Verfahren zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1557609A1 true EP1557609A1 (de) | 2005-07-27 |
EP1557609B1 EP1557609B1 (de) | 2016-03-16 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04001240.3A Expired - Lifetime EP1557609B1 (de) | 2004-01-21 | 2004-01-21 | Vorrichtung und Verfahren zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer |
Country Status (1)
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EP (1) | EP1557609B1 (de) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1762786A1 (de) * | 2005-09-13 | 2007-03-14 | Siemens Aktiengesellschaft | Verfahren und Vorrichtung zur Dämpfung thermo-akustischer Schwingungen, insbesondere in einer Gasturbine |
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 |
US10072843B2 (en) | 2015-10-21 | 2018-09-11 | Honeywell International Inc. | Combustion resonance suppression |
EP3434876A1 (de) * | 2017-07-25 | 2019-01-30 | Siemens Aktiengesellschaft | Brennkammervorrichtung und verfahren für den betrieb einer brennkammervorrichtung |
DE102005062284B4 (de) * | 2005-12-24 | 2019-02-28 | Ansaldo Energia Ip Uk Limited | Brennkammer für eine Gasturbine |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5431018A (en) * | 1992-07-03 | 1995-07-11 | Abb Research Ltd. | Secondary burner having a through-flow helmholtz resonator |
DE4414232A1 (de) | 1994-04-23 | 1995-10-26 | Abb Management Ag | Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer |
DE19640980A1 (de) | 1996-10-04 | 1998-04-16 | Asea Brown Boveri | Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer |
EP0974788A1 (de) | 1998-07-23 | 2000-01-26 | Asea Brown Boveri AG | Vorrichtung zur gezielten Schalldämpfung innerhalb einer Strömungsmaschine |
DE10004991A1 (de) | 2000-02-04 | 2001-08-09 | Volkswagen Ag | Helmholtz-Resonator mit variabler Resonanzfrequenz |
-
2004
- 2004-01-21 EP EP04001240.3A patent/EP1557609B1/de not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5431018A (en) * | 1992-07-03 | 1995-07-11 | Abb Research Ltd. | Secondary burner having a through-flow helmholtz resonator |
DE4414232A1 (de) | 1994-04-23 | 1995-10-26 | Abb Management Ag | Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer |
DE19640980A1 (de) | 1996-10-04 | 1998-04-16 | Asea Brown Boveri | Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer |
EP0974788A1 (de) | 1998-07-23 | 2000-01-26 | Asea Brown Boveri AG | Vorrichtung zur gezielten Schalldämpfung innerhalb einer Strömungsmaschine |
DE10004991A1 (de) | 2000-02-04 | 2001-08-09 | Volkswagen Ag | Helmholtz-Resonator mit variabler Resonanzfrequenz |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1762786A1 (de) * | 2005-09-13 | 2007-03-14 | Siemens Aktiengesellschaft | Verfahren und Vorrichtung zur Dämpfung thermo-akustischer Schwingungen, insbesondere in einer Gasturbine |
WO2007031376A1 (de) * | 2005-09-13 | 2007-03-22 | Siemens Aktiengesellschaft | Verfahren und vorrichtung zur dämpfung thermo-akustischer schwingungen, insbesondere in einer gasturbine |
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 |
US8919128B2 (en) | 2005-09-13 | 2014-12-30 | Siemens Aktiengesellschaft | Method and device for damping thermoacoustic oscillations, in particular in a gas turbine |
DE102005062284B4 (de) * | 2005-12-24 | 2019-02-28 | Ansaldo Energia Ip Uk Limited | Brennkammer für eine Gasturbine |
US8789372B2 (en) | 2009-07-08 | 2014-07-29 | General Electric Company | Injector with integrated resonator |
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 |
US10072843B2 (en) | 2015-10-21 | 2018-09-11 | Honeywell International Inc. | Combustion resonance suppression |
EP3434876A1 (de) * | 2017-07-25 | 2019-01-30 | Siemens Aktiengesellschaft | Brennkammervorrichtung und verfahren für den betrieb einer brennkammervorrichtung |
WO2019020474A1 (en) | 2017-07-25 | 2019-01-31 | Siemens Aktiengesellschaft | COMBUSTION APPARATUS AND METHOD OF OPERATION |
US20200141577A1 (en) * | 2017-07-25 | 2020-05-07 | 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 |
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EP1557609B1 (de) | 2016-03-16 |
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