EP0576717A1 - Chambre de combustion de turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz Download PDF

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Publication number
EP0576717A1
EP0576717A1 EP92111346A EP92111346A EP0576717A1 EP 0576717 A1 EP0576717 A1 EP 0576717A1 EP 92111346 A EP92111346 A EP 92111346A EP 92111346 A EP92111346 A EP 92111346A EP 0576717 A1 EP0576717 A1 EP 0576717A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
wall parts
flame tube
gas turbine
cooling air
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Withdrawn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
EP92111346A
Other languages
German (de)
English (en)
Inventor
Jakob Prof.Dr. Keller
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.)
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to EP92111346A priority Critical patent/EP0576717A1/fr
Priority to DE19934316475 priority patent/DE4316475C2/de
Publication of EP0576717A1 publication Critical patent/EP0576717A1/fr
Withdrawn legal-status Critical Current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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a gas turbine combustion chamber with a flame tube, which delimits a combustion chamber and is exposed on its side facing away from the combustion chamber to an air stream supplied by the compressor of the gas turbine, the flame tube essentially being composed of wall parts, and the outer wall parts facing away from the combustion chamber each having a plurality , Have circumferentially distributed inlet openings through which the cooling air is introduced into an intermediate space arranged in the flame tube, from which the cooling air is introduced into the combustion chamber via outlet openings in the inner wall parts facing the combustion chamber.
  • the invention has for its object in a gas turbine combustion chamber of the type mentioned at the minimum Cooling air consumption and a high pressure loss coefficient significantly increase the soundproofing of a combustion chamber wall.
  • this object is achieved according to the invention in that the space between the wall parts is coupled to a large, closed additional volume to form a Helmholtz resonator that the inlet openings in the outer wall parts are designed as feed pipes and the outlet openings in the inner wall parts are designed as damping pipes.
  • the damping system can thus be effectively integrated into the cooling system.
  • adequate damping of the combustion chamber vibrations can also be achieved. Since the resonance and thus the damping become weaker with larger amounts of cooling air, only enough cooling air is allowed to flow through that a significant heating of the resonator is avoided.
  • the turbine 1, of which the first axially flowed stages in the form of three guide rows 2 'and run rows 2' 'is shown in FIG. 1, essentially consists of the bladed turbine rotor 3 and the blade carrier 4 equipped with guide blades.
  • the blade carrier is in the Turbine housing 5 suspended.
  • the turbine housing 5 also includes the collecting space 6 for the compressed combustion air. From this plenum, the combustion air enters the annular combustion chamber 7, which in turn enters the turbine inlet, i.e. opens upstream of the first guide row 2 '.
  • the compressed air arrives in the collecting space from the diffuser 8 of the compressor 9. Of the latter, only the last three stages are shown in the form of three guide rows 10 'and rows 10' '.
  • the rotor blades of the compressor and the turbine sit on a common shaft 11, the central axis of which represents the longitudinal axis 12 of the gas turbine unit.
  • the compressed combustion air enters the collecting chamber 6 in the direction of the arrow in the burner 13, which is only shown as an example, of which 36 pieces are evenly distributed around the circumference.
  • the fuel is injected into the combustion chamber 15 via a fuel nozzle 14.
  • the fuel nozzle In the plane of the primary air inlet, the fuel nozzle is surrounded by a swirl body 16 in the form of vortex blades.
  • the air reaches the primary zone of the combustion chamber 15 through the vortex blades, in which the combustion process takes place.
  • the vortex blades cause one Swirl flow with an air core directed against the burner, which anchors the flame to the burner so that it does not tear off despite the high air speed.
  • the turbulent flow ensures rapid combustion.
  • the annular combustion chamber 15 extends downstream of the burner orifices up to the turbine inlet. It is delimited both inside and outside by the flame tube 17.
  • This flame tube can be designed as a self-supporting structure, it preferably consisting of a number of longitudinally arranged wall parts 18, 19 both on its inner ring and on its outer ring. These wall parts, which can be cast parts, are bent in the axial direction of the turbine in accordance with the course of the combustion chamber through which flow and extend over the entire axial length of the flame tube.
  • the flame tube on its side facing away from the combustion chamber is exposed to the air flow in the collecting chamber 6 supplied by the compressor 9.
  • the outer wall parts 18 have a plurality of inlet openings 20 distributed over the circumference, through which the cooling air is introduced into an intermediate space 21 formed in the flame tube.
  • these inlet openings 20 are impingement cooling bores through which the inflowing air reaches the inside of the inner wall part 19 impacts and performs its cooling function there. This is the first cooling stage.
  • the second cooling stage is designed as film cooling.
  • the requirement also applies to the outlet openings in the inner wall part 19 that the cooling air is introduced into the combustion chamber 15 in order to maintain cooling film in such a way that it not only coincides in the same direction, but also in its direction as closely as possible in the direction of flow of the combustion gases near the wall of the flame tube.
  • these outlet openings 22 are shown as oblique bores for the sake of simplicity. It could also be overlapping bricks, as they are known from the combustion chamber construction.
  • a rinsed Helmholtz resonator is now to be used for sound attenuation. It can easily be seen that the space 21 between the two wall parts 18 and 19 alone has too little volume for this to achieve the correct frequency. The intermediate space 21 is therefore coupled to a large, closed additional volume 23 at a suitable location.
  • the inlet openings 20 in the outer wall parts 19 are designed as feed pipes and the outlet bores 22 in the inner wall parts 18 as damping pipes of the Helmholtz resonator.
  • the feed pipes 20 are dimensioned such that they cause a relatively high pressure drop for the cooling air flow.
  • the damping tubes 22, on the other hand, allow the cooling air to enter the interior of the combustion chamber with a low residual pressure drop.
  • the limitation of the pressure drop in the damping tubes results from the requirement that even with uneven pressure distribution on the inside of the combustion chamber wall, an adequate cooling air flow into the combustion chamber is always guaranteed. Of course, no one is allowed to Place hot gas in reverse direction to enter the cooling system.
  • the choice of the size of the additional volume 23 results from the requirement that the phase angle between the fluctuations in the cooling air mass flows through the openings of the outer and inner wall parts should be greater than or equal to ⁇ / 2.
  • this requirement means that the compensation volume should be at least so large that the Helmholtz frequency of the Helmholtz resonator, which is formed by the additional volume, the volume of the space and the cooling air openings, is at least that Frequency of the combustion chamber vibration to be damped reached.
  • the compensation volume of the Helmholtz resonator used is preferably designed for the lowest natural frequency of the combustion chamber. It is also possible to choose an even larger volume.
  • the basic features of a flow through a Helmholtz resonator as can be used in a combustion chamber, but also everywhere else, are shown in FIG. 3.
  • the resonator essentially consists of the feed tube 20a, the resonance volume 23a and the damping tube 22a.
  • the feed pipe 20a determines the pressure drop.
  • the speed at the end of the feed pipe, the dynamic pressure of the jet together with the losses corresponds to the pressure drop across the combustion chamber. Only enough air is supplied that the interior of the damper does not heat up. Heating by radiation from the area of the combustion chamber would result in the frequency not remaining stable. The flushing should therefore only dissipate the radiated heat. So far, Helmholtz resonators are known.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
EP92111346A 1992-07-03 1992-07-03 Chambre de combustion de turbine à gaz Withdrawn EP0576717A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP92111346A EP0576717A1 (fr) 1992-07-03 1992-07-03 Chambre de combustion de turbine à gaz
DE19934316475 DE4316475C2 (de) 1992-07-03 1993-05-17 Gasturbinen-Brennkammer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92111346A EP0576717A1 (fr) 1992-07-03 1992-07-03 Chambre de combustion de turbine à gaz

Publications (1)

Publication Number Publication Date
EP0576717A1 true EP0576717A1 (fr) 1994-01-05

Family

ID=8209778

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92111346A Withdrawn EP0576717A1 (fr) 1992-07-03 1992-07-03 Chambre de combustion de turbine à gaz

Country Status (2)

Country Link
EP (1) EP0576717A1 (fr)
DE (1) DE4316475C2 (fr)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0597138A1 (fr) * 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
EP0716268A2 (fr) * 1994-12-09 1996-06-12 ABB Management AG Partie de paroi refroidi
EP0971172A1 (fr) * 1998-07-10 2000-01-12 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs
EP0990851A1 (fr) * 1998-09-30 2000-04-05 Asea Brown Boveri AG Chambre de combustion pour une turbine à gaz
US6170265B1 (en) 1997-07-15 2001-01-09 Abb Search Ltd. Method and device for minimizing thermoacoustic vibrations in gas-turbine combustion chambers
US6351947B1 (en) 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
WO2002025174A1 (fr) * 2000-09-21 2002-03-28 Siemens Westinghouse Power Corporation Resonateurs modulaires permettant de supprimer les instabilites de combustion dans des centrales electriques de turbine a gaz
WO2003023281A1 (fr) * 2001-09-07 2003-03-20 Alstom Technology Ltd Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
WO2004003434A1 (fr) * 2002-06-28 2004-01-08 Alexandre Kozyrev Chambre a combustion de moteur thermique
US6705428B2 (en) 2000-12-08 2004-03-16 Abb Turbo Systems Ag Exhaust gas system with helmholtz resonator
US6907736B2 (en) * 2001-01-09 2005-06-21 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor having an acoustic energy absorbing wall
EP1568869A1 (fr) * 2002-12-02 2005-08-31 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
US6973790B2 (en) 2000-12-06 2005-12-13 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, gas turbine, and jet engine
EP1666795A1 (fr) * 2004-11-24 2006-06-07 Rolls-Royce Plc Atténuateur acoustique
EP1832812A2 (fr) * 2006-03-10 2007-09-12 Rolls-Royce Deutschland Ltd & Co KG Paroi de chambre de combustion de turbine à gaz avec amortissement des vibrations de la chambre de combustion
US7857094B2 (en) * 2006-06-01 2010-12-28 Rolls-Royce Plc Combustion chamber for a gas turbine engine
EP2273196A2 (fr) 2009-07-08 2011-01-12 Rolls-Royce Deutschland Ltd & Co KG Tête pour chambre de combustion d'une turbine à gaz
EP2559942A1 (fr) 2011-08-19 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Tête de chambre de combustion d'une turbine à gaz dotée d'un refroidissement et d'un amortissement
WO2013029984A3 (fr) * 2011-09-01 2013-12-27 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
CN103620307A (zh) * 2011-07-07 2014-03-05 三菱重工业株式会社 燃气轮机燃烧器
CN104566457A (zh) * 2013-10-28 2015-04-29 阿尔斯通技术有限公司 用于燃气涡轮的阻尼器
RU2568030C2 (ru) * 2012-10-24 2015-11-10 Альстом Текнолоджи Лтд Демпфирующее устройство для уменьшения пульсаций камеры сгорания
US10197275B2 (en) 2016-05-03 2019-02-05 General Electric Company High frequency acoustic damper for combustor liners
US10513984B2 (en) 2015-08-25 2019-12-24 General Electric Company System for suppressing acoustic noise within a gas turbine combustor
WO2022191878A1 (fr) * 2021-03-08 2022-09-15 Raytheon Company Atténuateurs pour bruit de combustion dans des statoréacteurs à double mode et des statoréacteurs à combustion supersonique
CN115682033A (zh) * 2021-07-28 2023-02-03 北京航空航天大学 防振燃烧室以及燃烧室防振方法

Families Citing this family (6)

* 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
DE19640980B4 (de) * 1996-10-04 2008-06-19 Alstom Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
DE10026121A1 (de) * 2000-05-26 2001-11-29 Alstom Power Nv Vorrichtung zur Dämpfung akustischer Schwingungen in einer Brennkammer
DE102006011248A1 (de) * 2006-03-10 2007-09-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand mit Dämpfung von Brennkammerschwingungen mit integrierter Kühlung
DE102006011247A1 (de) * 2006-03-10 2007-09-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand mit Dämpfung von Brennkammerschwingungen
DE102006026969A1 (de) 2006-06-09 2007-12-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer

Citations (2)

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Publication number Priority date Publication date Assignee Title
US4077205A (en) * 1975-12-05 1978-03-07 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
GB2225381A (en) * 1988-11-25 1990-05-30 Gen Electric Noise suppressor for gas flows

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3978662A (en) * 1975-04-28 1976-09-07 General Electric Company Cooling ring construction for combustion chambers
FR2490786A1 (fr) * 1980-09-25 1982-03-26 Centre Nat Rech Scient Procede de commande d'une flamme de combustion et sonde microphonique permettant sa mise en oeuvre

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4077205A (en) * 1975-12-05 1978-03-07 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
GB2225381A (en) * 1988-11-25 1990-05-30 Gen Electric Noise suppressor for gas flows

Cited By (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0597138B1 (fr) * 1992-11-09 1997-07-16 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz
EP0597138A1 (fr) * 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
EP0716268A2 (fr) * 1994-12-09 1996-06-12 ABB Management AG Partie de paroi refroidi
EP0716268A3 (fr) * 1994-12-09 1998-12-23 Asea Brown Boveri Ag Partie de paroi refroidi
US6170265B1 (en) 1997-07-15 2001-01-09 Abb Search Ltd. Method and device for minimizing thermoacoustic vibrations in gas-turbine combustion chambers
EP0971172A1 (fr) * 1998-07-10 2000-01-12 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
US6430933B1 (en) 1998-09-10 2002-08-13 Alstom Oscillation attenuation in combustors
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs
EP0990851A1 (fr) * 1998-09-30 2000-04-05 Asea Brown Boveri AG Chambre de combustion pour une turbine à gaz
US6351947B1 (en) 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
WO2002025174A1 (fr) * 2000-09-21 2002-03-28 Siemens Westinghouse Power Corporation Resonateurs modulaires permettant de supprimer les instabilites de combustion dans des centrales electriques de turbine a gaz
US7549506B2 (en) 2000-09-21 2009-06-23 Siemens Energy, Inc. Method of suppressing combustion instabilities using a resonator adopting counter-bored holes
US7194862B2 (en) 2000-09-21 2007-03-27 Siemens Power Generation, Inc. Resonator adopting counter-bored holes and method of suppressing combustion instabilities
US6973790B2 (en) 2000-12-06 2005-12-13 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, gas turbine, and jet engine
US6705428B2 (en) 2000-12-08 2004-03-16 Abb Turbo Systems Ag Exhaust gas system with helmholtz resonator
US6907736B2 (en) * 2001-01-09 2005-06-21 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor having an acoustic energy absorbing wall
WO2003023281A1 (fr) * 2001-09-07 2003-03-20 Alstom Technology Ltd Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
US7104065B2 (en) 2001-09-07 2006-09-12 Alstom Technology Ltd. Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system
WO2004003434A1 (fr) * 2002-06-28 2004-01-08 Alexandre Kozyrev Chambre a combustion de moteur thermique
EP1568869A1 (fr) * 2002-12-02 2005-08-31 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
EP1568869A4 (fr) * 2002-12-02 2014-02-26 Mitsubishi Heavy Ind Ltd Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
US7549290B2 (en) 2004-11-24 2009-06-23 Rolls-Royce Plc Acoustic damper
EP1666795A1 (fr) * 2004-11-24 2006-06-07 Rolls-Royce Plc Atténuateur acoustique
EP1832812A3 (fr) * 2006-03-10 2012-01-04 Rolls-Royce Deutschland Ltd & Co KG Paroi de chambre de combustion de turbine à gaz avec amortissement des vibrations de la chambre de combustion
EP1832812A2 (fr) * 2006-03-10 2007-09-12 Rolls-Royce Deutschland Ltd & Co KG Paroi de chambre de combustion de turbine à gaz avec amortissement des vibrations de la chambre de combustion
US7857094B2 (en) * 2006-06-01 2010-12-28 Rolls-Royce Plc Combustion chamber for a gas turbine engine
US8677757B2 (en) 2009-07-08 2014-03-25 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head of a gas turbine
DE102009032277A1 (de) 2009-07-08 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerkopf einer Gasturbine
EP2273196A2 (fr) 2009-07-08 2011-01-12 Rolls-Royce Deutschland Ltd & Co KG Tête pour chambre de combustion d'une turbine à gaz
US10197284B2 (en) 2011-07-07 2019-02-05 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
CN103620307A (zh) * 2011-07-07 2014-03-05 三菱重工业株式会社 燃气轮机燃烧器
US9003800B2 (en) 2011-07-07 2015-04-14 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
CN103620307B (zh) * 2011-07-07 2015-08-12 三菱日立电力系统株式会社 燃气轮机燃烧器
EP2559942A1 (fr) 2011-08-19 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Tête de chambre de combustion d'une turbine à gaz dotée d'un refroidissement et d'un amortissement
WO2013029984A3 (fr) * 2011-09-01 2013-12-27 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
CN103765107A (zh) * 2011-09-01 2014-04-30 西门子公司 用于燃气轮机设备的燃烧室
CN103765107B (zh) * 2011-09-01 2016-05-04 西门子公司 用于燃气轮机设备的燃烧室
US10718520B2 (en) 2012-10-24 2020-07-21 Ansaldo Energia Switzerland AG Damper arrangement for reducing combustion-chamber pulsation
RU2568030C2 (ru) * 2012-10-24 2015-11-10 Альстом Текнолоджи Лтд Демпфирующее устройство для уменьшения пульсаций камеры сгорания
EP2865947A1 (fr) * 2013-10-28 2015-04-29 Alstom Technology Ltd Amortisseur pour turbines à gaz
US10036327B2 (en) 2013-10-28 2018-07-31 Ansaldo Energia Switzerland AG Damper with bent neck for gas turbine
CN104566457A (zh) * 2013-10-28 2015-04-29 阿尔斯通技术有限公司 用于燃气涡轮的阻尼器
US10513984B2 (en) 2015-08-25 2019-12-24 General Electric Company System for suppressing acoustic noise within a gas turbine combustor
US10197275B2 (en) 2016-05-03 2019-02-05 General Electric Company High frequency acoustic damper for combustor liners
WO2022191878A1 (fr) * 2021-03-08 2022-09-15 Raytheon Company Atténuateurs pour bruit de combustion dans des statoréacteurs à double mode et des statoréacteurs à combustion supersonique
CN115682033A (zh) * 2021-07-28 2023-02-03 北京航空航天大学 防振燃烧室以及燃烧室防振方法

Also Published As

Publication number Publication date
DE4316475A1 (de) 1994-01-05
DE4316475C2 (de) 2002-11-28

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