EP1624251A1 - dispositif pour atténuer les oscillations acoustiques dans les chambres combustion avec fréquence de résonance ajustable - Google Patents

dispositif pour atténuer les oscillations acoustiques dans les chambres combustion avec fréquence de résonance ajustable Download PDF

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Publication number
EP1624251A1
EP1624251A1 EP04018395A EP04018395A EP1624251A1 EP 1624251 A1 EP1624251 A1 EP 1624251A1 EP 04018395 A EP04018395 A EP 04018395A EP 04018395 A EP04018395 A EP 04018395A EP 1624251 A1 EP1624251 A1 EP 1624251A1
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EP
European Patent Office
Prior art keywords
resonator
neck
control
combustion chamber
resonator neck
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
Application number
EP04018395A
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German (de)
English (en)
Other versions
EP1624251B1 (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
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP04018395A priority Critical patent/EP1624251B1/fr
Publication of EP1624251A1 publication Critical patent/EP1624251A1/fr
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Publication of EP1624251B1 publication Critical patent/EP1624251B1/fr
Not-in-force legal-status Critical Current
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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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • 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 present invention relates to a device for damping acoustic oscillations in combustion chambers of a gas turbine with a resonator with variable resonance frequency, as well as a gas turbine.
  • a gas turbine plant comprises in the simplest case a compressor, a combustion chamber and a turbine.
  • the compressor there is a compression of sucked air, which is then admixed with a fuel.
  • the combustion chamber the mixture is combusted, the combustion exhaust gases being supplied to the turbine, from which energy is withdrawn from the combustion exhaust gases and converted into mechanical energy.
  • thermoacoustic oscillations in the combustors of gas turbines - or turbomachines in general - present a problem in the design and operation of new combustors, combustor parts and burners for such gas turbines.
  • the exhaust gases produced during the combustion process have a high temperature.
  • the combustion exhaust gases are therefore diluted with cooling air to lower the temperature to a level acceptable for the combustion chamber wall and the turbine components.
  • dilution can lead to higher emissions of pollutants.
  • the cooling air mass flow is in modern systems reduced. This also reduces the acoustic damping, so that thermoacoustic vibrations can increase. This can lead to a aufschaukelnden interaction between thermal and acoustic disturbances that bring high loads of the combustion chamber with it and can partially cancel the reduction of pollutant emissions.
  • thermoacoustic oscillations In particular, by the use of different fuels, but also in the partial load range or e.g. when starting the system, the frequencies shift under which increased thermoacoustic vibrations occur. If the damping device remains the same, it then does not work in the most favorable operating point calculated in advance and can no longer optimally damp the occurring thermoacoustic oscillations. This leads in addition to the disadvantages already described also to a higher noise pollution.
  • the object of the present invention is therefore to provide a device for damping thermoacoustic oscillations in combustion chambers of gas turbines, wherein the resonant frequency for damping thermoacoustic oscillations in gas turbines can be changed with structurally simple means.
  • thermoacoustic oscillations in combustion chambers of a gas turbine according to claim 1 and by a gas turbine according to claim 9.
  • the dependent claims contain advantageous embodiments of the invention.
  • a device for damping thermoacoustic oscillations, in particular thermoacoustic oscillations in a combustion chamber of a gas turbine, comprises at least one Helmholtz resonator whose resonant frequency is variable.
  • the Helmholtz resonator has a resonator neck, wherein at least one dimension of the resonator neck is variable.
  • a dimension of the resonator neck is directly influenced. Because a dimension of the resonator neck can be changed directly, the frequency of the resonator can be adjusted by simple means. In the known state of the art, however, the outer dimension of the resonator neck remains unchanged.
  • the effective cross-sectional area of the resonator neck can be changed. This can be achieved in particular by the fact that the cross-sectional area of the resonator neck itself is variable.
  • the resonator neck advantageously comprises at least one or more resonator tubes. In particular, at least the cross-sectional area of at least one resonator tube is then variable.
  • At least the effective length of the resonator neck is variable.
  • the length of one or more tubes forming the resonator neck is variable.
  • a tube can be made shorter and / or extendable. This can be done for example via two couplable parts that can be connected in series to extend the resonator neck or shorten.
  • a change of both the cross section and the length of the resonator neck can be made to set the resonant frequency of the Helmholtz resonator.
  • the resonator neck comprises at least two resonator tubes.
  • each of the tubes ends on one side in the resonator chamber and preferably on the other side in the combustion chamber.
  • the resonator neck is formed by two, three or more resonator tubes.
  • one of the resonator tubes can be closed in order to change the frequency.
  • f c / ( 2 ⁇ ) ( S / ( L V ) ) 1 ⁇ 2 describe.
  • c is the speed of sound in the medium
  • V the volume of the resonator chamber
  • L the length
  • S the cross-sectional area of the resonator neck.
  • the resonance frequency is reduced, and vice versa.
  • the resonance frequency is also reduced and increased by shortening.
  • a partial closing of the resonator neck as a whole or of one or more resonator tubes is also possible. This can e.g. be realized by changing the free flow cross-section of one or more resonator tubes.
  • the dimensions of the individual resonator tubes may be the same or different. It is possible that only the dimension of one of a plurality of resonator tubes is changeable.
  • the adjustment of the resonator can be possible in all embodiments manually with a suitable tool or by hand after opening the turbine housing. Even if this can be done only during the standstill of the machine, the adjustment with a relatively low installation effort is feasible, especially compared to the cost of replacing entire resonators.
  • At least one movable control element is provided, which cooperates with the resonator neck.
  • the control element cooperates with the opening of at least one resonator tube.
  • the control is movable, in particular it is rotatable and / or displaceable.
  • a controlled adjustment of the dimension (s) of the resonator neck takes place by means of a control device.
  • the adjustment can also be done automatically and also regulated. It is possible, for example, an electric motor, which moves the respective control to one or more Adjust the dimensions of the resonator neck.
  • the use of a hydraulic actuator is possible.
  • Particularly preferred is a controlled adjustment, so that an automatic adjustment of the control is effected in dependence on the determined thermoacoustic oscillations. Then an effective damping can be ensured within the control range.
  • the inventive manual or automatic adjustability is particularly advantageous in the prototype testing and also during commissioning.
  • a significant advantage of the ease of adjustability results not only from the operation with different fuels, but also under widely varying operating conditions, e.g. due to significant ambient temperature changes.
  • the control element may have one or more control openings, e.g. have different dimensions.
  • control openings e.g. have different dimensions.
  • control openings with different diameters and / or different lengths are possible.
  • control openings of different dimensions cooperate with at least one opening of the resonator neck.
  • control element has a substantially conical shape.
  • Preferred is e.g. an embodiment as a pin with a substantially conical end 15, which forms a closure cone.
  • Preferred developments are those in which the position of the control element can be controlled and / or regulated from the outside.
  • the object of the invention is also achieved by a gas turbine with a device according to the invention for damping thermoacoustic oscillations.
  • FIG. 1 shows a first exemplary embodiment of the device according to the invention for damping acoustic vibrations in a combustion chamber of a gas turbine.
  • the device 1 comprises a Helmholtz resonator 2, which has a resonator chamber 3 and a resonator neck 4, via which the Helmholtz resonator 2 is connected to a combustion chamber of a gas turbine.
  • the Helmholtz resonator 2 is designed substantially cylindrically symmetrical with respect to a longitudinal or central axis. However, embodiments are also possible which have no symmetry.
  • the resonator neck 4 is formed in total by three independent resonator tubes 5, 6 and 7, which, viewed from the combustion chamber, protrude into the resonator chamber 3.
  • the three resonator tubes have a tube length 5a, 6a and 7a, respectively.
  • the tube length is the same in each case.
  • the cross-sectional area of the resonator neck 4 is influenced by the individual open cross-sectional areas 5b, 6b, 7b of the three independent resonator tubes 5, 6 and 7.
  • a partial closing of one or more of the resonator tubes 5, 6, 7 changes the effective cross-sectional area of the resonator neck 4, which is composed of the cross-sectional areas 5b, 6b and 7b. It is thus possible to adjust the resonator frequency.
  • a control disk 8 is provided, which is rotatably mounted about a rotation axis 12.
  • the axis of rotation 12 and the central center axis coincide.
  • the cross-sectional areas 5b, 6b, 7b of the three resonator tubes 5, 6 and 7 are different in this embodiment.
  • the largest cross-sectional area 5b has the resonator tube 5, the smallest cross-sectional area 7b the resonator tube. 7
  • control disk 8 On the control disk 8 openings 9, 10 and 11 are provided, which are axially aligned with the resonator tubes 5, 6 and 7 are aligned by the control disk 8 is rotated accordingly. With different cross-sectional areas of the resonator tubes 5, 6 and 7, a resonator tube or a plurality of resonator tubes 5, 6, 7 can then be opened by targeted rotation of the control disc 8, while the remaining resonator tubes remain closed in order to adapt the resonant frequency to the given conditions.
  • the control disk is arranged in the resonator chamber 3 in total.
  • the adjustment can be made during breaks by means of a suitable tool by hand or during operation.
  • a controller (not shown) is provided, by means of which an adjustment can be controlled.
  • An automatic adjustment or regulation is possible. This can be done online during the operation. With a fully automatic control can take place a continuous or at intervals, adjustment to the strongest vibration frequency.
  • the cross-sectional areas 5b, 6b and 7b of the resonator tubes 5, 6 and 7 may also be the same in other embodiments.
  • By partially or completely opening a second or third resonator tube the cross section of the resonator neck 4 as a whole is varied, and a suitable attenuation frequency can be set.
  • a dimension of the resonator neck 4 is changed.
  • the cross-sectional area of the resonator neck 4 is increased, which increases the resonance frequency of the Helmholtz resonator 2. Therefore, by changing a dimension of the resonator neck, an effective change in the resonant frequency of the resonator is possible, so that the resonator 2 can be adapted to the vibrations to be damped. As a result, changed conditions, such as an altered fuel composition, reacts and an adjustment of the resonant frequency are performed.
  • the device 1 comprises a Helmholtz resonator 2 with a resonator chamber 3 and a resonator neck 4, which in turn is formed by three resonator tubes 5, 6 and 7, which also here have different cross sections.
  • the control is designed here as a control slide 13. Instead of a spool 13 but can also be used a rotatable camshaft.
  • the openings 9, 10 and 11 By means of the control slide 13, the openings 9, 10 and 11, a targeted opening and closing of the three resonator tubes 5, 6 and 7 is possible.
  • a targeted influencing of the cross section of the three resonator tubes By a targeted influencing of the cross section of the three resonator tubes, a dimension of the resonator neck 4 can be effectively changed, whereby the resonance frequency of the resonator 2 is changed.
  • the spool 13 may be performed through a side opening in the Helmholtz resonator 2 and displaced along the control direction 14. It is also possible, the control slide 13 is completely received by the Helmholtz resonator 2 in all control positions.
  • FIG. 3 shows a third embodiment, in which also a device 1 with a Helmholtz resonator 2, which has a resonator 3 and a resonator neck 4, is provided.
  • the resonator neck 4 in this exemplary embodiment comprises only a single resonator tube 5.
  • a targeted change of the effective flow cross-section of the resonator tube 5 is possible by means of a control cone 15.
  • the control cone 15 is moved along the control direction 16.
  • the resonator tube 5 partially - or completely if necessary - are closed.
  • an annular gap remains open.
  • the effective flow cross section depends on how deep the control cone 15 is lowered into the resonator tube 5. Changing the effective flow area affects the resonant frequency.
  • a plurality of resonator tubes 5 may also be provided, e.g. two, three, four or more, each having an adjustable by means of a control cone effective flow cross-section.
  • a respective Helmholtz resonator 2 with a resonator chamber 3 and a resonator neck 4 formed by a respective resonator tube 5 is shown.
  • the length of the resonator neck 4 is influenced, as a result of which an effective frequency change of the resonator 2 is likewise possible.
  • control element is a control disk 17 rotatable about an axis of rotation 18 and in the example according to FIG. 5 a control valve 23 is provided as a control element, which is displaceable along a control direction 24.
  • the thickness of the control disk 17 varies over its circumference, while the thickness of the control slide varies over its length. The change in thickness can take place continuously or in stages.
  • through holes 9, 10 and 11 are present, for example. Can be realized as through holes.
  • the respective control element 17 or 23 has a thickness 20, at the location of a second bore 10 a thickness 21 and at the location of a third bore 11 a thickness 22, wherein the thickness 22 is greater than the thickness 21 and the thickness 20 has the smallest dimension.
  • the respective bores can be brought into a position aligned with the resonator tube 5.
  • the first bore 9 is shown in alignment with the resonator tube 5.
  • the resonator neck 4 in this case has a total length 25, which results from the length 19 of the resonator tube 5 and the thickness 20 of the control disk 17 and the spool 23, that is, the length of the respective aligned hole 9.
  • the total length 25 results as the sum of the length 19 and the thickness 21, and when adjusted to the opening or bore 11 results in the total length 25 as the sum of the length 19 and the thickness 22nd
  • control discs or spools may be present with more than three openings, in which each opening has a different length.

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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)
  • Exhaust Silencers (AREA)
EP04018395A 2004-08-03 2004-08-03 Dispositif pour atténuer les oscillations acoustiques dans les chambres combustion avec fréquence de résonance ajustable Not-in-force EP1624251B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04018395A EP1624251B1 (fr) 2004-08-03 2004-08-03 Dispositif pour atténuer les oscillations acoustiques dans les chambres combustion avec fréquence de résonance ajustable

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Application Number Priority Date Filing Date Title
EP04018395A EP1624251B1 (fr) 2004-08-03 2004-08-03 Dispositif pour atténuer les oscillations acoustiques dans les chambres combustion avec fréquence de résonance ajustable

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EP1624251A1 true EP1624251A1 (fr) 2006-02-08
EP1624251B1 EP1624251B1 (fr) 2012-02-29

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699322A1 (de) * 2008-08-14 2010-02-15 Alstom Technology Ltd Verfahren zum einstellen eines helmholtz-resonators sowie helmholtz-resonator zur durchführung des verfahrens.
CN101619713B (zh) * 2009-08-11 2011-04-20 深圳市中科力函热声技术工程研究中心有限公司 具有螺旋流道谐振管的热声发动机
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
EP2397760A1 (fr) 2010-06-16 2011-12-21 Alstom Technology Ltd Agencement d'amortisseur et procédé pour le concevoir
US20140109591A1 (en) * 2012-10-24 2014-04-24 Alstom Technology Ltd. Damper arrangement for reducing combustion-chamber pulsation
US9097179B2 (en) 2009-05-05 2015-08-04 Rolls-Royce Plc Damping assembly
EP3153777A1 (fr) * 2015-10-05 2017-04-12 General Electric Technology GmbH Ensemble amortisseur pour une chambre de combustion
EP3156664A1 (fr) * 2015-10-13 2017-04-19 Alcatel Lucent Ensemble résonateur réglable et procédé pour réduire des émissions acoustiques dans un système d'écoulement de gaz
FR3065754A1 (fr) * 2017-04-28 2018-11-02 Safran Aircraft Engines Cellule d'absorption acoustique pour turboreacteur et panneau de traitement acoustique associe

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4414232A1 (de) * 1994-04-23 1995-10-26 Abb Management Ag Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
EP0723123A1 (fr) * 1995-01-23 1996-07-24 Nefit Fasto B.V. Système de combustion insonorisée et amortisseur pour un tel système
DE10004991A1 (de) * 2000-02-04 2001-08-09 Volkswagen Ag Helmholtz-Resonator mit variabler Resonanzfrequenz
DE10058688A1 (de) * 2000-11-25 2003-01-02 Alstom Switzerland Ltd Dämpferanordnung zur Reduktion von Brennkammerpulsationen
WO2004051063A1 (fr) * 2002-12-02 2004-06-17 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4414232A1 (de) * 1994-04-23 1995-10-26 Abb Management Ag Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
EP0723123A1 (fr) * 1995-01-23 1996-07-24 Nefit Fasto B.V. Système de combustion insonorisée et amortisseur pour un tel système
DE10004991A1 (de) * 2000-02-04 2001-08-09 Volkswagen Ag Helmholtz-Resonator mit variabler Resonanzfrequenz
DE10058688A1 (de) * 2000-11-25 2003-01-02 Alstom Switzerland Ltd Dämpferanordnung zur Reduktion von Brennkammerpulsationen
WO2004051063A1 (fr) * 2002-12-02 2004-06-17 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010018069A1 (fr) 2008-08-14 2010-02-18 Alstom Technology Ltd. Procédé pour régler un résonateur de helmholtz et résonateur de helmholtz destiné à mettre en œuvre le procédé
JP2011530689A (ja) * 2008-08-14 2011-12-22 アルストム テクノロジー リミテッド ヘルムホルツ共鳴器の調節のための方法及び該方法の実施のためのヘルムホルツ共鳴器
US8205714B2 (en) 2008-08-14 2012-06-26 Alstom Technology Ltd. Method for adjusting a Helmholtz resonator and an adjustable Helmholtz resonator
CH699322A1 (de) * 2008-08-14 2010-02-15 Alstom Technology Ltd Verfahren zum einstellen eines helmholtz-resonators sowie helmholtz-resonator zur durchführung des verfahrens.
US9097179B2 (en) 2009-05-05 2015-08-04 Rolls-Royce Plc Damping assembly
CN101619713B (zh) * 2009-08-11 2011-04-20 深圳市中科力函热声技术工程研究中心有限公司 具有螺旋流道谐振管的热声发动机
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
EP2397760A1 (fr) 2010-06-16 2011-12-21 Alstom Technology Ltd Agencement d'amortisseur et procédé pour le concevoir
JP2012002500A (ja) * 2010-06-16 2012-01-05 Alstom Technology Ltd ダンパ機構およびこのダンパを構成するための方法
US8727070B2 (en) 2010-06-16 2014-05-20 Alstom Technology Ltd Helmholtz damper and method for regulating the resonance frequency of a Helmholtz damper
US8931589B2 (en) 2010-06-16 2015-01-13 Alstom Technology Ltd. Damper arrangement and method for designing same
US20140109591A1 (en) * 2012-10-24 2014-04-24 Alstom Technology Ltd. Damper arrangement for reducing combustion-chamber pulsation
US10718520B2 (en) * 2012-10-24 2020-07-21 Ansaldo Energia Switzerland AG Damper arrangement for reducing combustion-chamber pulsation
EP3153777A1 (fr) * 2015-10-05 2017-04-12 General Electric Technology GmbH Ensemble amortisseur pour une chambre de combustion
US10100688B2 (en) 2015-10-05 2018-10-16 Ansaldo Energia Switzerland AG Damper assembly for a combustion chamber
EP3156664A1 (fr) * 2015-10-13 2017-04-19 Alcatel Lucent Ensemble résonateur réglable et procédé pour réduire des émissions acoustiques dans un système d'écoulement de gaz
FR3065754A1 (fr) * 2017-04-28 2018-11-02 Safran Aircraft Engines Cellule d'absorption acoustique pour turboreacteur et panneau de traitement acoustique associe
US10557417B2 (en) 2017-04-28 2020-02-11 Safran Aircraft Engines Acoustic absorber cell for a turbojet, and an associated acoustic treatment panel

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