EP2383515A1 - Système de brûleur et procédé d'amortissement d'un tel système de brûleur - Google Patents

Système de brûleur et procédé d'amortissement d'un tel système de brûleur Download PDF

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Publication number
EP2383515A1
EP2383515A1 EP10161306A EP10161306A EP2383515A1 EP 2383515 A1 EP2383515 A1 EP 2383515A1 EP 10161306 A EP10161306 A EP 10161306A EP 10161306 A EP10161306 A EP 10161306A EP 2383515 A1 EP2383515 A1 EP 2383515A1
Authority
EP
European Patent Office
Prior art keywords
burner
head end
hat
combustion chamber
plenum
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
EP10161306A
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German (de)
English (en)
Other versions
EP2383515B1 (fr
Inventor
Sven Bethke
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.)
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 EP10161306.5A priority Critical patent/EP2383515B1/fr
Priority to RU2012103903/06A priority patent/RU2541478C2/ru
Priority to US13/388,347 priority patent/US8631654B2/en
Priority to CN201180003126.9A priority patent/CN102472495B/zh
Priority to PCT/EP2011/053356 priority patent/WO2011134706A1/fr
Priority to JP2013506557A priority patent/JP5409959B2/ja
Publication of EP2383515A1 publication Critical patent/EP2383515A1/fr
Application granted granted Critical
Publication of EP2383515B1 publication Critical patent/EP2383515B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • 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 invention relates to a burner system having at least two adjacent burners, each having at least one combustion chamber and a head end, the latter comprising at least one fuel injection and a fuel-air premix, each burner having a hat with a hat side and a hat top, wherein at least the Hutoberseite seen in the flow direction is arranged in front of the head end, wherein between the Hutoberseite and the head end thereby a burner plenum is formed. Furthermore, the invention relates to a method for damping vibrations of such a burner system.
  • thermoacoustically induced combustion oscillations can occur. These arise through an interaction of the combustion flame and the associated heat release with acoustic pressure fluctuations.
  • acoustic excitation By means of an acoustic excitation, the position of the flame, the flame front surface or the mixture composition can fluctuate, which in turn leads to fluctuations of the heat release. With a constructive phase position, positive feedback and amplification can occur. Such an increased combustion vibration can lead to considerable noise and vibration damage.
  • thermoacoustically induced instabilities are significantly influenced by the acoustic properties of the combustion chamber and the boundary conditions present at the combustion chamber inlet and the combustion chamber outlet as well as at the combustion chamber walls.
  • the acoustic properties can be changed by installing Helmholtz resonators.
  • the WO 93/10401 A1 shows a device for suppressing combustion oscillations in a combustion chamber of a gas turbine plant.
  • a Helmholtz resonator is fluidically connected to a fuel supply line. The acoustic properties of the supply line or the overall acoustic system are thereby changed so that combustion oscillations are suppressed.
  • this measure is not sufficient in all operating conditions, as it can lead to combustion oscillations even with a suppression of vibrations in the fuel line.
  • the WO 03 / 074936A1 shows a gas turbine, with a burner which opens into a combustion chamber, said mouth is annularly surrounded by a Helmholtz resonator.
  • a gas turbine with a burner which opens into a combustion chamber, said mouth is annularly surrounded by a Helmholtz resonator.
  • combustion vibrations are effectively attenuated by close contact with the flame, while avoiding temperature nonuniformity.
  • Helmholtz resonator tubes are mounted, which cause a frequency adjustment.
  • a gas turbine combustor which has air-purged Helmholtz resonators in the burner.
  • the resonators are arranged alternately on the end face of the combustion chamber between the burners. By these resonators, vibration energy is absorbed by combustion vibrations occurring in the combustion chamber and the combustion vibrations are thereby damped.
  • Each of these resonators has functionally a connecting opening with the combustion chamber, which must be blocked by a certain amount of air. This amount of air is, when attaching the resonators on the combustion chamber wall, then no longer available for combustion, as it is passed by the burner. This increases the flame temperature and NOx emissions.
  • the object of the present invention is therefore to specify a burner system which can be used for damping combustion oscillations and which avoids the above problem. Another object is to specify a method which can be used to dampen combustion oscillations and which avoids the above problem.
  • a burner system is provided with at least two adjacent burners, each having at least one combustion chamber and a head end, the latter comprising at least one fuel injection and a fuel-air premix.
  • each burner has a hat with a hat side and a hat top, wherein at least the hat top side is arranged in the flow direction in front of the head end. Between the Hutoberseite and the head end of a burner plenum is formed.
  • the acoustic analysis of the acoustic pressure distributions shows that this results in a mode shape in which adjacent combustion chambers, including the plenums, oscillate out of phase upstream of the combustion chambers.
  • the at least two burner plenums now have an acoustic connection.
  • the hat side is at least partially arranged around the head end, so that in this case the hat side is spaced in a radial direction from the head end.
  • a channel is formed by the hat side and the head end. Through this channel compressor air is directed to the plenum. This compressor air thus cools the outside of the combustion chamber and thus reduces overheating of the combustion chamber. Ideally, the compressor air is preheated so that a more stable combustion can take place.
  • the acoustic connection is a burner plenums connecting pipe, in particular a ringfömig trained pipe or a channel.
  • This connection is particularly easy to implement constructively.
  • Each burner with its burner plenum preferably has an acoustic connection to the respectively adjacent burners or burner plenums.
  • a gas turbine comprises such a burner system.
  • the method-related object is achieved by the disclosure of a method for damping vibrations of a burner system, comprising at least two adjacent burners, each having at least one combustion chamber and a head end, the latter comprising at least one fuel injection and a fuel-air premix, wherein each burner has a hat with a hat side and a hat top, wherein at least the Hutoberseite seen in the flow direction is arranged in front of the head end, wherein between the Hutoberseite and the head end thereby a burner plenum is formed and whereby an acoustic connection between two adjacent burner Plenen an opposite-phase oscillation of the adjacent burner and its burner plenen is avoided.
  • thermoacoustic vibrations By this method are simplified thermoacoustic vibrations largely prevented or even avoided. Thus, in contrast to the prior art, various frequencies occurring can be damped.
  • FIG. 1 shows by way of example a gas turbine 1 in a longitudinal partial section.
  • the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3 with a shaft, which is also referred to as a turbine runner.
  • a compressor 5 for example a toroidal combustion chamber 6, in particular pipe or annular combustion chamber, with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing.
  • the combustion chamber 6 communicates with, for example, a ring-shaped hot gas channel 11.
  • a turbine stage 12 connected in series form the turbine 8.
  • Each turbine stage 12 is formed for example of two blade rings. As seen in the direction of flow of a working medium 13, a row 25 of blades 25 follows in the hot gas channel 11 of a row of guide vanes 15.
  • the burner 7 in conjunction with a so-called tube combustion chamber 6 ( Fig. 2 ) used.
  • the gas turbine 1 has a plurality of annularly arranged tube combustion chambers 6, whose outflow openings open into the annular hot gas channel 11 turbine inlet side.
  • a plurality, for example six or eight, burner 7 is arranged at the opposite end of the downstream opening of the tube combustion chamber 6 usually annularly around a pilot burner.
  • FIG. 2 shows a section of a tube burner 7 schematically.
  • the burner 7 comprises a head end 51, a transition 52 and a liner 53 therebetween.
  • the "head end 51” is essentially the subsection of the fuel injection 55 / fuel-air premix 56 of the burner.
  • the liner 53 extends from the head end to the transition 52 in any manner.
  • an annular passage 57 is formed by the combustion / cooling air 65 flows.
  • Fuel / air premix 56 is referred to as burner plenum (plenum) 100.
  • the burner 7 has a hat 110 with a hat side 150 and a hat top 170.
  • at least the hat top side 170 is arranged upstream of the head end 51, as seen in the flow direction, whereby a burner plenum 100 is formed between the hat top side 170 and the head end 51.
  • the hat 110 has a combustion chamber-facing side 140 and a combustion chamber-facing side 120 (FIG. Fig. 3 ).
  • the hat 110 with the hat side 150 is arranged virtually outside the machine.
  • Fig. 3 shows the burner system according to the invention with two adjacent burners 7, each of which has a tube combustion chamber 6 and a head end 51.
  • Each of the burners 7 has a hat 110 with a hat side 150 and a hat top 170.
  • at least the hat top side 170 is arranged upstream of the head end 51, as seen in the flow direction, whereby a burner plenum 100 is formed between the hat top side 170 and the head end 51.
  • An acoustic connection 130 is present between the two adjacent burner plenums 100.
  • This acoustic connection is here advantageously annular and thus connects the respective adjacent burner plenums 100 of the burner 7 the entire gas turbine with each other.
  • the annular connection can be realized for example by means of a tube that connects the individual planks 100 with each other. In the area of plenums 100 such a connection 130 can be realized without great constructive effort.
  • the annular connection thus ends at the burner plenum 100 at which it has begun. It no longer fades in modes that spread over the connection in front of the turbine from one combustion chamber to the other, so that the combustion chambers oscillate with their plumes in phase opposition.
  • the acoustic connection 130 suppresses and prevents the formation of such a mode shape.
EP10161306.5A 2010-04-28 2010-04-28 Système de brûleur pour l'amortissement d'un tel système de brûleur Not-in-force EP2383515B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP10161306.5A EP2383515B1 (fr) 2010-04-28 2010-04-28 Système de brûleur pour l'amortissement d'un tel système de brûleur
RU2012103903/06A RU2541478C2 (ru) 2010-04-28 2011-03-07 Система форсунок и способ демпфирования такой системы форсунок
US13/388,347 US8631654B2 (en) 2010-04-28 2011-03-07 Burner system and method for damping such a burner system
CN201180003126.9A CN102472495B (zh) 2010-04-28 2011-03-07 燃烧器系统和这种燃烧器系统的阻尼方法
PCT/EP2011/053356 WO2011134706A1 (fr) 2010-04-28 2011-03-07 Système de combustion et procédé pour amortir les vibrations d'un tel système de combustion
JP2013506557A JP5409959B2 (ja) 2010-04-28 2011-03-07 バーナ装置及びこの種のバーナの振動減衰方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10161306.5A EP2383515B1 (fr) 2010-04-28 2010-04-28 Système de brûleur pour l'amortissement d'un tel système de brûleur

Publications (2)

Publication Number Publication Date
EP2383515A1 true EP2383515A1 (fr) 2011-11-02
EP2383515B1 EP2383515B1 (fr) 2013-06-19

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP10161306.5A Not-in-force EP2383515B1 (fr) 2010-04-28 2010-04-28 Système de brûleur pour l'amortissement d'un tel système de brûleur

Country Status (6)

Country Link
US (1) US8631654B2 (fr)
EP (1) EP2383515B1 (fr)
JP (1) JP5409959B2 (fr)
CN (1) CN102472495B (fr)
RU (1) RU2541478C2 (fr)
WO (1) WO2011134706A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2474784A1 (fr) * 2011-01-07 2012-07-11 Siemens Aktiengesellschaft Système de combustion pour turbine à gaz comprenant un résonateur
US8684130B1 (en) * 2012-09-10 2014-04-01 Alstom Technology Ltd. Damping system for combustor
JP6075263B2 (ja) * 2013-10-04 2017-02-08 株式会社デンソー 車両用吸気装置
CN106631905A (zh) * 2016-12-29 2017-05-10 江苏华亘泰来生物科技有限公司 13c尿素加工方法
JP7262364B2 (ja) * 2019-10-17 2023-04-21 三菱重工業株式会社 ガスタービン燃焼器
CN113739202B (zh) * 2021-09-13 2023-04-25 中国联合重型燃气轮机技术有限公司 具有调整热声震荡功能的罩帽

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993010401A1 (fr) 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
EP0597138A1 (fr) 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
WO2003074936A1 (fr) 2002-03-07 2003-09-12 Siemens Aktiengesellschaft Turbine a gaz
JP2005048992A (ja) * 2003-07-31 2005-02-24 Tokyo Electric Power Co Inc:The ガスタービン燃焼器
EP1703208A1 (fr) * 2005-02-04 2006-09-20 Enel Produzione S.p.A. Amortissement des oscillations thermoacoustiques dans des chambres de combustion de turbine à gaz avec chambre annulaire
EP2154434A1 (fr) * 2007-06-11 2010-02-17 Mitsubishi Heavy Industries, Ltd. Structure de montage de dispositif de détection d'oscillation de combustion

Family Cites Families (9)

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Publication number Priority date Publication date Assignee Title
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
DE19851636A1 (de) * 1998-11-10 2000-05-11 Asea Brown Boveri Dämpfungsvorrichtung zur Reduzierung der Schwingungsamplitude akustischer Wellen für einen Brenner
RU2175743C2 (ru) * 1999-02-10 2001-11-10 Государственное предприятие Научно-исследовательский институт машиностроения Способ газодинамического воспламенения и устройство для его осуществления
RU2200869C2 (ru) * 2000-10-16 2003-03-20 Меринов Александр Генадьевич Форсунка для впрыска топлива с форкамерой
US7832211B2 (en) * 2002-12-02 2010-11-16 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor and a gas turbine equipped therewith
US6931833B2 (en) * 2003-04-30 2005-08-23 United Technologies Corporation Pulse combustion device
EP1762786A1 (fr) * 2005-09-13 2007-03-14 Siemens Aktiengesellschaft Procédé et appareil pour réduire les vibrations thermo-accoustiques, en particulier dans une turbine
RU2386825C2 (ru) * 2008-06-16 2010-04-20 Александр Сергеевич Артамонов Способ работы многотопливного теплового двигателя и компрессора и устройство для его осуществления (варианты)
RU2387582C2 (ru) * 2008-06-18 2010-04-27 Александр Сергеевич Артамонов Комплекс для реактивного полета

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993010401A1 (fr) 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
EP0597138A1 (fr) 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
WO2003074936A1 (fr) 2002-03-07 2003-09-12 Siemens Aktiengesellschaft Turbine a gaz
JP2005048992A (ja) * 2003-07-31 2005-02-24 Tokyo Electric Power Co Inc:The ガスタービン燃焼器
EP1703208A1 (fr) * 2005-02-04 2006-09-20 Enel Produzione S.p.A. Amortissement des oscillations thermoacoustiques dans des chambres de combustion de turbine à gaz avec chambre annulaire
EP2154434A1 (fr) * 2007-06-11 2010-02-17 Mitsubishi Heavy Industries, Ltd. Structure de montage de dispositif de détection d'oscillation de combustion

Also Published As

Publication number Publication date
JP2013525737A (ja) 2013-06-20
JP5409959B2 (ja) 2014-02-05
CN102472495B (zh) 2014-07-09
WO2011134706A1 (fr) 2011-11-03
CN102472495A (zh) 2012-05-23
EP2383515B1 (fr) 2013-06-19
RU2541478C2 (ru) 2015-02-20
US20120291438A1 (en) 2012-11-22
US8631654B2 (en) 2014-01-21
RU2012103903A (ru) 2013-08-10

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