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EP2397759A1 - Damper Arrangement - Google Patents

Damper Arrangement Download PDF

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Publication number
EP2397759A1
EP2397759A1 EP10166095A EP10166095A EP2397759A1 EP 2397759 A1 EP2397759 A1 EP 2397759A1 EP 10166095 A EP10166095 A EP 10166095A EP 10166095 A EP10166095 A EP 10166095A EP 2397759 A1 EP2397759 A1 EP 2397759A1
Authority
EP
European Patent Office
Prior art keywords
entrance portion
damper arrangement
volume
damper
helmholtz
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Withdrawn
Application number
EP10166095A
Other languages
German (de)
French (fr)
Inventor
Andreas Huber
Nicolas Noiray
Bruno Schürmans
Mirko Bothien
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP10166095A priority Critical patent/EP2397759A1/en
Publication of EP2397759A1 publication Critical patent/EP2397759A1/en
Withdrawn legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002Wall structures
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23MCASINGS, 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
    • F23M20/00Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005Noise absorbing means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D2210/00Noise abatement
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to a damper arrangement.
  • the damper arrangement is used to damp pressure oscillations that are generated during operation of a gas turbine provided with a lean premixed, low emission combustion system.
  • Gas turbines are known to comprise one or more combustion chambers, wherein a fuel is injected, mixed to an air flow and combusted, to generate high pressure flue gases that are expanded in a turbine.
  • pressure oscillations may be generated that could cause mechanical damages to the combustion chamber and limit the operating regime.
  • combustion chambers are provided with damping devices, such as quarter wave tubes, Helmholtz dampers or acoustic screens, to damp these pressure oscillations.
  • damping devices such as quarter wave tubes, Helmholtz dampers or acoustic screens
  • traditional Helmholtz dampers 1 include a damping volume 2 (i.e. a resonator volume) and an entrance portion or neck 3 to be connected to a combustion chamber 5, wherein combustion occurs and pressure oscillations to be damped may be generated (reference 4 indicates the wall of the combustion chamber 5) .
  • a damping volume 2 i.e. a resonator volume
  • an entrance portion or neck 3 to be connected to a combustion chamber 5, wherein combustion occurs and pressure oscillations to be damped may be generated (reference 4 indicates the wall of the combustion chamber 5) .
  • the resonance frequency (i.e. the damped frequency) of the Helmholtz damper depends on the geometrical features of the damping volume 2 and entrance portion 3 (neck) and must correspond to the frequency of the pressure oscillations generated in the combustion chamber 5.
  • the damping frequency bandwidth of the Helmholtz dampers 1 is very narrow, such that in case one single Helmholtz damper is used, it could not be able to cover the whole frequency bandwidth of the pressure oscillations that are generated in the combustion chamber 5.
  • Helmholtz dampers 1 are connected to the combustion chamber 5.
  • a Helmholtz damper in order to efficiently damp pressure oscillations having a fixed frequency, a Helmholtz damper must be located at the position of the combustion chamber where that pressure oscillations have maximum amplitude.
  • DE102005062284 discloses a combustion chamber with a damper arrangement including several Helmholtz dampers connected in series.
  • the technical aim of the present invention therefore includes providing a damper arrangement addressing the aforementioned problems of the known art.
  • an aspect of the invention is to provide a damper arrangement, which is able to damp pressure oscillations having different frequencies at the same location.
  • Another aspect of the invention is to provide a damper arrangement, which is quite compact and, in other words, requires a limited space, in particular when compared to traditional Helmholtz dampers connected in series.
  • the damper arrangement 10 comprises a first damping volume 11 with a first entrance portion or neck 12 connectable to a chamber 13 wherein pressure oscillations to be damped may be generated.
  • the chamber 13 may be the combustion chamber of a gas turbine.
  • the arrangement 10 has a second damping volume 15 with a second entrance portion or neck 16.
  • the second entrance portion 16 is housed within the first entrance portion 12.
  • first and the second entrance portions 12, 16 are defined by a first and a second tubular part that are preferably coaxial with each other.
  • the mouth 18 of the tubular part defining the second entrance portion 16 is flush with the mouth 19 of the tubular part defining the first entrance portion 12 (i.e. they are aligned and in particular the mouth 18 does not protrudes from the mouth 19).
  • the second damping volume 15 is included (i.e. housed) within the first damping volume 11. Nevertheless in different embodiments it could also be external or partially external to it; for example the wall defining the first damping volume 11 could have a hole through which the second volume 15, or also the first entrance portion 16, passes.
  • first volume 11 and the first entrance portion 12 define a Helmholtz damper and the second volume 15 and the second entrance portion 16 also define a Helmholtz damper (embodiment shown in figure 2 ).
  • first volume 11 and the first entrance portion 12 define a Helmholtz damper and the second volume 15 and the second entrance portion 16 define a quarter wave tube (embodiment shown in figure 3 ).
  • first volume 11 and the first entrance portion 12 may define a quarter wave tube and the second volume 15 and the second entrance portion 16 may also define a quarter wave tube (embodiment not shown).
  • first entrance portion 12 and/or the second entrance portion 16 may be provided with means 20 to enhance viscous dissipation (in order to increase damping efficiency).
  • figure 4 shows an entrance portion 16; it is clear that even if this particular example is described and shown, also different embodiments are possible and the means 20 may be provided at the entrance portion 12 in addition to or instead of the entrance portion 16. Moreover also the entrance portion of a quarter wave tube (in case it is provided) may be provided with the means 20.
  • Figure 5 shows a first embodiment of the means 20 to enhance viscous dissipation being a perforated plate.
  • the means 20 may also be a vortex generator.
  • Figures 6 and 7 show a further embodiment in which the means 20 are arranged to increase the inner surface of the entrance portion 16; in this case the means 20 may define a cross section such as a star shaped cross section (eventually by introducing into the entrance portion 16 a holed cylinder having internal walls with the required shape, as shown in the enclosed figures 6 and 7 ).
  • Figure 8 shows a further example in which the means 20 comprise additional plates housed in the entrance portion 16.
  • means 21 to reduce the flow resistance may also be provided at the entrance portion 16 and/or 12, both in case the damper arrangement comprises Helmholtz dampers and/or quarter wave tubes.
  • These means 21 could comprise rounded inlet and/or outlet of the entrance portions ( figures 9 and 10 ).
  • cooling holes may be provided, to allow cooling air 23 to enter the first and/or second volume 11 and/or 15.

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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)

Abstract

The damper arrangement (10) comprises a first damping volume (11) with a first entrance portion (12) connectable to a chamber (13) wherein pressure oscillations to be damped may be generated. The damping arrangement (10) also has a second damping volume (15) with a second entrance portion (16). The second entrance portion (16) is housed within the first entrance portion (12).

Description

    TECHNICAL FIELD
  • The present invention relates to a damper arrangement.
  • In particular, the damper arrangement is used to damp pressure oscillations that are generated during operation of a gas turbine provided with a lean premixed, low emission combustion system.
  • BACKGROUND OF THE INVENTION
  • Gas turbines are known to comprise one or more combustion chambers, wherein a fuel is injected, mixed to an air flow and combusted, to generate high pressure flue gases that are expanded in a turbine.
  • During operation, pressure oscillations may be generated that could cause mechanical damages to the combustion chamber and limit the operating regime.
  • For this reason, usually combustion chambers are provided with damping devices, such as quarter wave tubes, Helmholtz dampers or acoustic screens, to damp these pressure oscillations.
  • With reference to figure 1, traditional Helmholtz dampers 1 include a damping volume 2 (i.e. a resonator volume) and an entrance portion or neck 3 to be connected to a combustion chamber 5, wherein combustion occurs and pressure oscillations to be damped may be generated (reference 4 indicates the wall of the combustion chamber 5) .
  • The resonance frequency (i.e. the damped frequency) of the Helmholtz damper depends on the geometrical features of the damping volume 2 and entrance portion 3 (neck) and must correspond to the frequency of the pressure oscillations generated in the combustion chamber 5.
  • Nevertheless, at the low frequency range the damping frequency bandwidth of the Helmholtz dampers 1 is very narrow, such that in case one single Helmholtz damper is used, it could not be able to cover the whole frequency bandwidth of the pressure oscillations that are generated in the combustion chamber 5.
  • It is clear that in this case some of the pressure oscillations would not be damped, with a detrimental effect on the gas turbine structure and operation.
  • In order to damp pressure oscillations in a bandwidth sufficiently large, typically a number of Helmholtz dampers 1 are connected to the combustion chamber 5.
  • Nevertheless, also in this case problems may arise.
  • In fact, in order to efficiently damp pressure oscillations having a fixed frequency, a Helmholtz damper must be located at the position of the combustion chamber where that pressure oscillations have maximum amplitude.
  • It is clear that when a combustion chamber has the pressure oscillations with different frequencies having maximum amplitude at the same location or at locations close to one another, different Helmholtz dampers having different features should be installed at that location.
  • Nevertheless, in combustion chambers of gas turbines the locations where Helmholtz dampers can be connected are limited and, thus, it is usually not possible to connect different Helmholtz dampers at the same location (for example angularly shifted from one another).
  • DE102005062284 discloses a combustion chamber with a damper arrangement including several Helmholtz dampers connected in series.
  • This arrangement allows different frequencies to be addressed, but it is very demanding in terms of space.
  • SUMMARY OF THE INVENTION
  • The technical aim of the present invention therefore includes providing a damper arrangement addressing the aforementioned problems of the known art.
  • Within the scope of this technical aim, an aspect of the invention is to provide a damper arrangement, which is able to damp pressure oscillations having different frequencies at the same location.
  • Another aspect of the invention is to provide a damper arrangement, which is quite compact and, in other words, requires a limited space, in particular when compared to traditional Helmholtz dampers connected in series.
  • The technical aim, together with these and further aspects, are attained according to the invention by providing a damper arrangement in accordance with the accompanying claims.
  • BRIEF DESCRIPTION OF THE DRAWINGS
  • Further characteristics and advantages of the invention will be more apparent from the description of a preferred but non-exclusive embodiment of the damper arrangement illustrated by way of non-limiting example in the accompanying drawings, in which:
    • Figure 1 is a schematic view of a Helmholtz damper according to the prior art;
    • Figures 2 and 3 show two different embodiments of damper arrangements;
    • Figures 4 shows an entrance portion or neck of a Helmholtz damper;
    • Figure 5 shows means to enhance viscous dissipation included in the embodiment of figure 4;
    • Figures 6 shows a further entrance portion or neck of a Helmholtz damper;
    • Figure 7 shows a cross section of the entrance portion or neck of figure 6;
    • Figure 8 shows a further different cross section of an entrance portion or neck; and
    • Figures 9 and 10 show further different embodiments of
    the entrance portion or neck. DETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION
  • The damper arrangement 10 comprises a first damping volume 11 with a first entrance portion or neck 12 connectable to a chamber 13 wherein pressure oscillations to be damped may be generated.
  • Thus, for example, the chamber 13 may be the combustion chamber of a gas turbine.
  • The arrangement 10 has a second damping volume 15 with a second entrance portion or neck 16.
  • The second entrance portion 16 is housed within the first entrance portion 12.
  • In particular, the first and the second entrance portions 12, 16 are defined by a first and a second tubular part that are preferably coaxial with each other.
  • In addition, the mouth 18 of the tubular part defining the second entrance portion 16 is flush with the mouth 19 of the tubular part defining the first entrance portion 12 (i.e. they are aligned and in particular the mouth 18 does not protrudes from the mouth 19).
  • As shown in the figures, the second damping volume 15 is included (i.e. housed) within the first damping volume 11. Nevertheless in different embodiments it could also be external or partially external to it; for example the wall defining the first damping volume 11 could have a hole through which the second volume 15, or also the first entrance portion 16, passes.
  • In particular, the first volume 11 and the first entrance portion 12 define a Helmholtz damper and the second volume 15 and the second entrance portion 16 also define a Helmholtz damper (embodiment shown in figure 2).
  • Alternatively, the first volume 11 and the first entrance portion 12 define a Helmholtz damper and the second volume 15 and the second entrance portion 16 define a quarter wave tube (embodiment shown in figure 3).
  • Also further embodiments are possible and, for example, the first volume 11 and the first entrance portion 12 may define a quarter wave tube and the second volume 15 and the second entrance portion 16 may also define a quarter wave tube (embodiment not shown).
  • Advantageously the first entrance portion 12 and/or the second entrance portion 16 may be provided with means 20 to enhance viscous dissipation (in order to increase damping efficiency).
  • In particular, figure 4 shows an entrance portion 16; it is clear that even if this particular example is described and shown, also different embodiments are possible and the means 20 may be provided at the entrance portion 12 in addition to or instead of the entrance portion 16. Moreover also the entrance portion of a quarter wave tube (in case it is provided) may be provided with the means 20.
  • Figure 5 shows a first embodiment of the means 20 to enhance viscous dissipation being a perforated plate. Alternatively, the means 20 may also be a vortex generator.
  • Figures 6 and 7 show a further embodiment in which the means 20 are arranged to increase the inner surface of the entrance portion 16; in this case the means 20 may define a cross section such as a star shaped cross section (eventually by introducing into the entrance portion 16 a holed cylinder having internal walls with the required shape, as shown in the enclosed figures 6 and 7).
  • Figure 8 shows a further example in which the means 20 comprise additional plates housed in the entrance portion 16.
  • Alternatively, means 21 to reduce the flow resistance may also be provided at the entrance portion 16 and/or 12, both in case the damper arrangement comprises Helmholtz dampers and/or quarter wave tubes.
  • These means 21 could comprise rounded inlet and/or outlet of the entrance portions (figures 9 and 10).
  • This can lead to higher oscillation amplitudes in the entrance portion and thus an increase of damping effect.
  • In order to cool the components of the damper arrangement, cooling holes may be provided, to allow cooling air 23 to enter the first and/or second volume 11 and/or 15.
  • The operation of the damper arrangement of the invention is apparent from that described and illustrated and is substantially the following.
  • When during gas turbine operation pressure oscillations are generated, they cause gas to move in and out the entrance portions 12 and 16; this makes the pressure oscillations damp.
  • Since the entrance portions 12, 16 have the same or substantially the same location, also pressure oscillations having different frequencies with peaks at the same or close locations can be addressed.
  • Naturally, the features described may be independently provided from one another.
  • In practice, the materials used and the dimensions can be chosen at will according to requirements and to the state of the art.
  • REFERENCE NUMBERS
  • 1
    Helmholtz damper
    2
    damping volume
    3
    entrance portion or neck
    4
    wall
    5
    combustion chamber
    10
    damp arrangement
    11
    first volume
    12
    first entrance or neck
    13
    chamber
    15
    second volume
    16
    second entrance or neck
    18
    mouth of 16
    19
    mouth of 12
    20
    means to enhance viscous dissipation
    21
    means to reduce the flow resistance
    23
    cooling air

Claims (10)

  1. Damper arrangement (10) comprising a first damping volume (11) with a first entrance portion (12) connectable to a chamber (13) wherein pressure oscillations to be damped may generate, characterised by comprising a second damping volume (15) with a second entrance portion (16), wherein the second entrance portion (16) is housed within the first entrance portion (12).
  2. Damper arrangement (10) as claimed in claim 1, characterised in that the first and the second entrance portion (12, 16) are defined respectively by a first and a second tubular part.
  3. Damper arrangement (10) as claimed in claim 2, characterised in that the tubular part defining the first entrance portion (12) and the tubular part defining the second entrance portion (16) are coaxial with each other.
  4. Damper arrangement (10) as claimed in claim 2, characterised in that the mouth (18) of the tubular part defining the second entrance portion (16) is flush with the mouth (19) of the tubular part defining the first entrance portion (12).
  5. Damper arrangement (10) as claimed in claim 1, characterised in that the second damping volume (15) is included in the first damping volume (11).
  6. Damper arrangement (10) as claimed in claim 1, characterised in that the first entrance portion (12) and/or the second entrance portion (16) are provided with means (20) to enhance viscous dissipation.
  7. Damper arrangement (10) as claimed in claim 1, characterised in that the first entrance portion (12) and/or the second entrance portion (16) are provided with means (21) to reduce the flow resistance.
  8. Damper arrangement (10) as claimed in claim 1, characterised in that the first volume (11) and the first entrance portion (12) define a Helmholtz damper.
  9. Damper arrangement (10) as claimed in claim 8, characterised in that the second volume (15) and the second entrance portion (16) define a Helmholtz damper.
  10. Damper arrangement (10) as claimed in claim 8, characterised in that the second volume (15) and the second entrance portion (16) define a quarter wave tube.
EP10166095A 2010-06-16 2010-06-16 Damper Arrangement Withdrawn EP2397759A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10166095A EP2397759A1 (en) 2010-06-16 2010-06-16 Damper Arrangement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10166095A EP2397759A1 (en) 2010-06-16 2010-06-16 Damper Arrangement

Publications (1)

Publication Number Publication Date
EP2397759A1 true EP2397759A1 (en) 2011-12-21

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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2642204A1 (en) * 2012-03-21 2013-09-25 Alstom Technology Ltd Simultaneous broadband damping at multiple locations in a combustion chamber
US20130283799A1 (en) * 2012-04-25 2013-10-31 Solar Turbines Inc. Resonance damper for damping acoustic oscillations from combustor
EP2725300A1 (en) * 2012-10-24 2014-04-30 Alstom Technology Ltd Damper arrangement for reducing combustion-chamber pulsations
EP2735796A1 (en) * 2012-11-23 2014-05-28 Alstom Technology Ltd Insert element for closing an opening inside a wall of a hot gas path component of a gas turbine and method for enhancing operational behaviour of a gas turbine
EP2837782A1 (en) * 2013-08-14 2015-02-18 Alstom Technology Ltd Damper for combustion oscillation damping in a gas turbine
WO2015023733A1 (en) * 2013-08-13 2015-02-19 General Electric Company Apparatus and method for dampening acoustics
EP3032177A1 (en) * 2014-12-11 2016-06-15 Alstom Technology Ltd Compensation assembly for a damper of a gas turbine
WO2017042250A1 (en) * 2015-09-08 2017-03-16 Siemens Aktiengesellschaft Gas turbine combustor liner with helmholtz damper
CN107003002A (en) * 2014-09-15 2017-08-01 通用电器技术有限公司 Combustor dome buffer system
US20180172273A1 (en) * 2016-12-16 2018-06-21 General Electric Company Fuel Nozzle with Narrow-Band Acoustic Damper
CN109899826A (en) * 2019-03-28 2019-06-18 苏州博墨热能产品有限公司 A method of resonance smoke box and its enhancing heat exchange
EP3663548A1 (en) * 2018-12-06 2020-06-10 Ansaldo Energia Switzerland AG Damper for a combustor assembly of a gas turbine power plant and combustor assembly comprising said damper
CN112178695A (en) * 2019-07-01 2021-01-05 安萨尔多能源瑞士股份公司 Damper, burner assembly comprising a damper and method of manufacturing a damper
DE102020200583A1 (en) 2020-01-20 2021-07-22 Siemens Aktiengesellschaft Resonator ring for combustion chamber systems

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JPH05215027A (en) * 1992-01-31 1993-08-24 Suzuki Motor Corp Wide band resonator
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JPH0921364A (en) * 1995-07-05 1997-01-21 Toyota Auto Body Co Ltd Resonator structure for vehicle
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DE102005062284A1 (en) 2005-12-24 2008-01-31 Alstom Technology Ltd. Combustion chamber for gas turbine of power plant system, has damping device that is formed as Helmholtz Resonator arrangement with helmholtz-Resonator including resonator area and resonator neck, and is attached to chamber through opening

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05215027A (en) * 1992-01-31 1993-08-24 Suzuki Motor Corp Wide band resonator
JPH0681737A (en) * 1992-08-28 1994-03-22 Yamaha Motor Co Ltd Air intake device for internal combustion engine
JPH0921364A (en) * 1995-07-05 1997-01-21 Toyota Auto Body Co Ltd Resonator structure for vehicle
EP0974788A1 (en) * 1998-07-23 2000-01-26 Asea Brown Boveri AG Device for directed noise attenuation in a turbomachine
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Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2642204A1 (en) * 2012-03-21 2013-09-25 Alstom Technology Ltd Simultaneous broadband damping at multiple locations in a combustion chamber
EP2828580A2 (en) * 2012-03-21 2015-01-28 Alstom Technology Ltd Simultaneous broadband damping at multiple locations in a combustion chamber
WO2013139868A3 (en) * 2012-03-21 2013-11-14 Alstom Technology Ltd Simultaneous broadband damping at multiple locations in a combustion chamber
US10546070B2 (en) 2012-03-21 2020-01-28 Ansaldo Energia Switzerland AG Simultaneous broadband damping at multiple locations in a combustion chamber
EP2828580B1 (en) * 2012-03-21 2021-07-14 Ansaldo Energia Switzerland AG Simultaneous broadband damping at multiple locations in a combustion chamber
JP2015518534A (en) * 2012-03-21 2015-07-02 アルストム テクノロジー リミテッドALSTOM Technology Ltd Simultaneous and broadband attenuation at multiple locations in the combustion chamber
US20130283799A1 (en) * 2012-04-25 2013-10-31 Solar Turbines Inc. Resonance damper for damping acoustic oscillations from combustor
CN103776061A (en) * 2012-10-24 2014-05-07 阿尔斯通技术有限公司 Damper assembly for reducing combustion-chamber pulsation
CN103776061B (en) * 2012-10-24 2017-01-04 通用电器技术有限公司 For reducing the muffler assembly of combustor pulsation
US10718520B2 (en) 2012-10-24 2020-07-21 Ansaldo Energia Switzerland AG Damper arrangement for reducing combustion-chamber pulsation
EP2725300A1 (en) * 2012-10-24 2014-04-30 Alstom Technology Ltd Damper arrangement for reducing combustion-chamber pulsations
US10330319B2 (en) 2012-10-24 2019-06-25 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas mixer
EP2735796A1 (en) * 2012-11-23 2014-05-28 Alstom Technology Ltd Insert element for closing an opening inside a wall of a hot gas path component of a gas turbine and method for enhancing operational behaviour of a gas turbine
US9631813B2 (en) 2012-11-23 2017-04-25 General Electric Technology Gmbh Insert element for closing an opening inside a wall of a hot gas path component of a gas turbine and method for enhancing operational behaviour of a gas turbine
WO2015023733A1 (en) * 2013-08-13 2015-02-19 General Electric Company Apparatus and method for dampening acoustics
CN105452773A (en) * 2013-08-13 2016-03-30 通用电气公司 Apparatus and method for dampening acoustics
US9970659B2 (en) 2013-08-14 2018-05-15 Ansaldo Energia Ip Uk Limited Damper for combustion oscillation damping in a gas turbine
EP2837782A1 (en) * 2013-08-14 2015-02-18 Alstom Technology Ltd Damper for combustion oscillation damping in a gas turbine
EP2837783A1 (en) * 2013-08-14 2015-02-18 Alstom Technology Ltd Damper for combustion oscillation damping in a gas turbine
CN107003002A (en) * 2014-09-15 2017-08-01 通用电器技术有限公司 Combustor dome buffer system
US10267523B2 (en) 2014-09-15 2019-04-23 Ansaldo Energia Ip Uk Limited Combustor dome damper system
CN105698217B (en) * 2014-12-11 2020-07-31 安萨尔多能源瑞士股份公司 Compensation assembly for a damper of a gas turbine
EP3032177A1 (en) * 2014-12-11 2016-06-15 Alstom Technology Ltd Compensation assembly for a damper of a gas turbine
US10527284B2 (en) 2014-12-11 2020-01-07 Ansaldo Energia Switzerland AG Compensation assembly for a damper of a gas turbine
CN105698217A (en) * 2014-12-11 2016-06-22 通用电器技术有限公司 Compensation assembly for a damper of a gas turbine
WO2017042250A1 (en) * 2015-09-08 2017-03-16 Siemens Aktiengesellschaft Gas turbine combustor liner with helmholtz damper
US20180172273A1 (en) * 2016-12-16 2018-06-21 General Electric Company Fuel Nozzle with Narrow-Band Acoustic Damper
US11041625B2 (en) * 2016-12-16 2021-06-22 General Electric Company Fuel nozzle with narrow-band acoustic damper
EP3663548A1 (en) * 2018-12-06 2020-06-10 Ansaldo Energia Switzerland AG Damper for a combustor assembly of a gas turbine power plant and combustor assembly comprising said damper
CN111288492A (en) * 2018-12-06 2020-06-16 安萨尔多能源瑞士股份公司 Damper for a burner assembly and burner assembly comprising said damper
CN111288492B (en) * 2018-12-06 2022-11-08 安萨尔多能源瑞士股份公司 Damper for a burner assembly and burner assembly comprising said damper
CN109899826A (en) * 2019-03-28 2019-06-18 苏州博墨热能产品有限公司 A method of resonance smoke box and its enhancing heat exchange
CN112178695A (en) * 2019-07-01 2021-01-05 安萨尔多能源瑞士股份公司 Damper, burner assembly comprising a damper and method of manufacturing a damper
EP3760925A1 (en) * 2019-07-01 2021-01-06 Ansaldo Energia Switzerland AG Damper for a combustor assembly of a gas turbine assembly, combustor assembly comprising said damper and method for manufacturing a damper for a combustor assembly
CN112178695B (en) * 2019-07-01 2024-07-26 安萨尔多能源瑞士股份公司 Damper, burner assembly including damper, and method of manufacturing damper
DE102020200583A1 (en) 2020-01-20 2021-07-22 Siemens Aktiengesellschaft Resonator ring for combustion chamber systems

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