EP1557609B1 - Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion - Google Patents

Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion Download PDF

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Publication number
EP1557609B1
EP1557609B1 EP04001240.3A EP04001240A EP1557609B1 EP 1557609 B1 EP1557609 B1 EP 1557609B1 EP 04001240 A EP04001240 A EP 04001240A EP 1557609 B1 EP1557609 B1 EP 1557609B1
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EP
European Patent Office
Prior art keywords
combustion chamber
resonator
openings
volume
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.)
Expired - Lifetime
Application number
EP04001240.3A
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German (de)
English (en)
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EP1557609A1 (fr
Inventor
Sven Dr. Bethke
Tobias Dr. Buchal
Michael Dr. Huth
Harald Nimptsch
Bernd Dr. Prade
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Siemens AG
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Siemens AG
Siemens Corp
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Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP04001240.3A priority Critical patent/EP1557609B1/fr
Publication of EP1557609A1 publication Critical patent/EP1557609A1/fr
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Publication of EP1557609B1 publication Critical patent/EP1557609B1/fr
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    • 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.
  • DE 44 14232A1 teaches a Helmholtz resonator for damping thermoacoustic oscillations in a combustion chamber of a gas turbine, the Helmholtz resonator has a resonating volume in connection with the gas turbine combustion chamber and comprises means for adjusting a flow of cooling air into the resonator volume.
  • DE 196 40 980 A teaches a Helmholtz resonator for damping thermoacoustic oscillations in a combustion chamber of a gas turbine, the Helmholtz resonator has a resonating volume in connection with the gas turbine combustion chamber and comprises means for feeding a constant flow of cooling air into the resonator volume to keep the temperature and the resonator frequency of the Helmholtz resonator constant.
  • EP 0 974 788 A teaches a Helmholtz resonator for damping thermoacoustic oscillations in a combustion chamber of a gas turbine, the Helmholtz resonator has a resonating volume in connection with the gas turbine combustion chamber and comprises means for adjusting a spray of water into the resonator volume.
  • 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 connectable 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, wherein
  • 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 with the suitable means mentioned above.
  • 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.
  • gas turbine combustion chamber incorporating the device of the present invention.
  • the gas turbine combustion chamber can be an annular combustion chamber.
  • 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 with a device 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 with a device as claimed in claim 1.
  • 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 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 valve 18 could also be connected to a 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)

Claims (7)

  1. Dispositif d'amortissement d'oscillations thermoacoustiques dans une chambre de combustion ( 10 ), comprenant un résonateur ( 11 ) d'Helmholtz, qui a un volume ( 23 ) résonnant pouvant communiquer avec la chambre ( 10 ) de combustion, comprenant
    des moyens pour régler un courant ( 14, 20 ) d'air de refroidissement allant dans le volume du résonateur, dans lequel
    - de l'air de refroidissement ( 14, 20 ) est introduit dans le volume ( 23 ) du résonateur par plusieurs ouvertures ( 12A, 12B ) placées sur le résonateur et la section transversale des ouvertures ( 12A, 12B ) est réglable de manière à pouvoir fermer complètement les ouvertures ( 12A, 12B ) afin de modifier le nombre d'ouvertures efficaces.
  2. Chambre de combustion ( 10 ) de turbine à gaz comprenant un dispositif suivant la revendication 1.
  3. Chambre de combustion ( 10 ) de turbine à gaz suivant la revendication 2, qui est une chambre de combustion annulaire.
  4. Procédé d'amortissement d'oscillations thermoacoustiques dans une chambre de combustion ( 10 ) par un dispositif comprenant un résonateur ( 11 ) d'Helmholtz ayant un volume ( 23 ) de résonateur pouvant communiquer avec la chambre de combustion ( 10 ), dans lequel
    on règle un courant ( 14, 20 ) d'air de refroidissement allant dans le volume ( 23 ) du résonateur par un dispositif tel que revendiqué à la revendication 1.
  5. Procédé suivant la revendication 4, dans lequel on règle le courant ( 14, 20 ) d'air de refroidissement allant dans le volume ( 23 ) du résonateur de manière à se rendre maître de la fréquence de résonance du résonateur ( 11 ) d'Helmholtz sur une large bande de fréquence.
  6. Procédé suivant la revendication 4 effectué dans une chambre de combustion ( 10 ) d'une turbine à gaz.
  7. Procédé suivant la revendication 4, comprenant une commande active d'instabilité, en particulier sous la forme d'un processus en boucle fermée.
EP04001240.3A 2004-01-21 2004-01-21 Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion Expired - Lifetime EP1557609B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04001240.3A EP1557609B1 (fr) 2004-01-21 2004-01-21 Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04001240.3A EP1557609B1 (fr) 2004-01-21 2004-01-21 Appareil et procédé d'amortissement des oscillations thermoacoustiques dans une chambre de combustion

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EP1557609A1 EP1557609A1 (fr) 2005-07-27
EP1557609B1 true EP1557609B1 (fr) 2016-03-16

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Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1762786A1 (fr) * 2005-09-13 2007-03-14 Siemens Aktiengesellschaft Procédé et appareil pour réduire les vibrations thermo-accoustiques, en particulier dans une 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 (fr) 2017-07-25 2019-01-30 Siemens Aktiengesellschaft Appareil de chambre de combustion et procédé de fonctionnement d'appareil de chambre de combustion

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59208193D1 (de) * 1992-07-03 1997-04-17 Abb Research Ltd Nachbrenner
DE4414232A1 (de) 1994-04-23 1995-10-26 Abb Management Ag Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
DE19640980B4 (de) 1996-10-04 2008-06-19 Alstom Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
EP0974788B1 (fr) 1998-07-23 2014-11-26 Alstom Technology Ltd Dispositif d'atténuation adaptée de bruit dans une turbomachine
DE10004991A1 (de) 2000-02-04 2001-08-09 Volkswagen Ag Helmholtz-Resonator mit variabler Resonanzfrequenz

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