EP1342953A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP1342953A1
EP1342953A1 EP02005137A EP02005137A EP1342953A1 EP 1342953 A1 EP1342953 A1 EP 1342953A1 EP 02005137 A EP02005137 A EP 02005137A EP 02005137 A EP02005137 A EP 02005137A EP 1342953 A1 EP1342953 A1 EP 1342953A1
Authority
EP
European Patent Office
Prior art keywords
resonator
burner
combustion chamber
combustion
gas turbine
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Withdrawn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
EP02005137A
Other languages
German (de)
English (en)
Inventor
Patrick Flohr
Werner Dr. Krebs
Bernd Dr. Prade
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP02005137A priority Critical patent/EP1342953A1/fr
Priority to CNB038045117A priority patent/CN1320314C/zh
Priority to JP2003573352A priority patent/JP4429730B2/ja
Priority to DE50309686T priority patent/DE50309686D1/de
Priority to US10/506,121 priority patent/US7246493B2/en
Priority to EP03706564A priority patent/EP1483536B1/fr
Priority to PCT/EP2003/001862 priority patent/WO2003074936A1/fr
Priority to ES03706564T priority patent/ES2303892T3/es
Publication of EP1342953A1 publication Critical patent/EP1342953A1/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Withdrawn legal-status Critical Current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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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 invention relates to a gas turbine with a burner which opens into a combustion chamber.
  • the combustion chamber is designed as an annular combustion chamber.
  • Combustion systems such as gas turbines, aircraft engines, rocket engines and heating systems can cause thermoacoustically induced combustion vibrations. These arise from an interaction of the combustion flame and the associated heat release with acoustic pressure fluctuations.
  • the position of the flame, the flame front surface or the mixture composition can fluctuate due to acoustic excitation, which in turn leads to fluctuations in the heat release. With a constructive phase position, positive feedback and amplification can occur. Such an increased combustion vibration can lead to considerable noise pollution and damage from vibrations.
  • thermoacoustically induced instabilities are significantly influenced by the acoustic properties of the combustion chamber and the boundary conditions at the combustion chamber inlet and outlet as well as on the combustion chamber walls.
  • the acoustic properties can be changed by installing Helmholtz resonators.
  • WO 93/10401 A1 shows a device for suppressing combustion vibrations in a combustion chamber of a gas turbine system.
  • a Helmholtz resonator is fluidly connected to a fuel supply line.
  • the acoustic properties of the supply line or of the overall acoustic system are changed such that combustion vibrations are suppressed.
  • this measure is not sufficient in all operating states, since it is also used to suppress vibrations Combustion vibrations can occur in the fuel line.
  • US-A-6 058 709 suggests introducing fuel at axially different positions in the combustion channel of a burner.
  • constructive phase positions in the mixture composition are superimposed by destructive ones with regard to the formation of combustion vibrations, so that overall there are lower fluctuations and thus a reduced tendency to form combustion vibrations.
  • This measure is, however, comparatively complex in terms of apparatus compared to the purely passive measure of using Helmholtz resonators.
  • EP 0 597 138 A1 describes a gas turbine combustion chamber which has air-purged Helmholtz resonators in the area of the burners.
  • the resonators are arranged alternately on the front side of the combustion chamber between the burners. These resonators absorb vibration energy from combustion vibrations occurring in the combustion chamber and the combustion vibrations are thereby damped.
  • the object of the invention is to provide a gas turbine with a particularly low tendency to form combustion vibrations.
  • this object is achieved by specifying a gas turbine with a combustion chamber and a burner opening into the combustion chamber at a burner mouth, the burner mouth being surrounded in a ring by a Helmholtz resonator.
  • the Helmholtz resonator preferably has a resonator volume and opens into the combustion chamber at a resonator mouth, the resonator mouth being continued with a tube into the resonator volume.
  • the resonator mouth is further preferably formed by a plurality of openings, each of which is continued into the resonator volume via a tube.
  • the tubes thus protrude into the resonator volume. This design makes it possible to keep the size of the resonator small.
  • a resonator usually consists of a volume V and bores of a certain length I and cross section A.
  • the projecting tubes can be used to dispense with increasing the volume of the resonator.
  • the tube or the tubes are preferably curved or twisted, so that the tube length is increased without being less than a minimum distance from the resonator wall.
  • the resonator volume is preferably adjustable, for example by a piston-like displacement of a resonator wall.
  • the acoustic properties in particular the impedance, can be adjusted and set.
  • the combustion chamber is designed as an annular combustion chamber.
  • combustion vibrations can lead to very disturbing and damaging combustion vibrations due to a comparatively large combustion chamber volume and burners coupled therein.
  • the acoustic properties of such a combustion chamber can hardly be calculated.
  • the Helmholtz resonator is preferably integrated in a burner insert, the burner being connected to the combustion chamber via the burner insert.
  • the burner insert can be a separate component that is screwed to the combustion chamber wall, for example, and in which the actual burner is then inserted. However, it can also be connected to the burner, so that, for example, the burner insert forms a flange on the burner with which the burner is connected to the combustion chamber wall.
  • the integration of the resonator in the burner insert means that no structural measures are required on the combustion chamber wall and the resonator can be easily removed if necessary.
  • the Helmholtz resonator is preferably designed to allow air to flow through it. In this way, the impedance of the resonator can be changed and adapted in a simple manner. In addition, cooling of the resonator and, if the resonator is integrated into the burner insert, cooling of the entire burner insert is also achieved.
  • a gas turbine 51 is shown in FIG.
  • the gas turbine 51 has a compressor 53, an annular combustion chamber 55 and a turbine part 57. Air 58 from the surroundings is fed to the compressor 53 and compressed there to combustion air 9. The combustion air 9 is then fed to the annular combustion chamber 55. It is burned there with fuel 11 to a hot gas 59 via gas turbine burner 1. The hot gas 59 drives the turbine part 57.
  • FIG. 2 shows a gas turbine burner 1, which is connected to a combustion chamber wall 56 of a combustion chamber 55 via a burner insert 2 and opens into the combustion chamber 55 at a burner mouth 4.
  • a burner duct 3 of the gas turbine burner 1 surrounds a central duct 41 as an annular duct 30.
  • the annular duct 30 is designed as a premixing duct in which fuel 11 and combustion air 9 are mixed intensively before combustion. This is known as premix combustion.
  • the fuel 11 is introduced into the ring channel 30 via swirl blades 13 of hollow design.
  • the central channel 41 opens into the combustion zone 27 together with a central fuel lance 45 which supplies fuel 47, in particular oil, via a swirl nozzle 47.
  • fuel 11 and combustion air 9 are only mixed in the combustion zone 27 and one speaks of a diffusion combustion.
  • fuel 11, in particular natural gas can also be added into the central channel 41 upstream of the combustion zone 27 via a fuel inlet 43.
  • a Helmholtz resonator 19 is integrated in the burner insert 2 and has a resonator volume 23 and opens into the combustion chamber 55 via a resonator mouth 21 consisting of bores.
  • a tube 61 adjoins each of the bores into the resonator volume 23 and is shaped in a twisted manner.
  • the Helmholtz resonator 19 surrounds the burner mouth 4 in a ring.
  • the tubes 61 allow a comparatively small size for the resonator 19, so that it can be integrated into the burner insert 2. Air is introduced into the resonator 19 via air inlets 63, whereby the impedance of the resonator 19 can be adjusted on the one hand, and can also be cooled on the other.

Landscapes

  • 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)
  • Gas Burners (AREA)
EP02005137A 2002-03-07 2002-03-07 Turbine à gaz Withdrawn EP1342953A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP02005137A EP1342953A1 (fr) 2002-03-07 2002-03-07 Turbine à gaz
CNB038045117A CN1320314C (zh) 2002-03-07 2003-02-24 燃气轮机
JP2003573352A JP4429730B2 (ja) 2002-03-07 2003-02-24 ガスタービン
DE50309686T DE50309686D1 (de) 2002-03-07 2003-02-24 Gasturbine
US10/506,121 US7246493B2 (en) 2002-03-07 2003-02-24 Gas turbine
EP03706564A EP1483536B1 (fr) 2002-03-07 2003-02-24 Turbine a gaz
PCT/EP2003/001862 WO2003074936A1 (fr) 2002-03-07 2003-02-24 Turbine a gaz
ES03706564T ES2303892T3 (es) 2002-03-07 2003-02-24 Turbina de gas.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02005137A EP1342953A1 (fr) 2002-03-07 2002-03-07 Turbine à gaz

Publications (1)

Publication Number Publication Date
EP1342953A1 true EP1342953A1 (fr) 2003-09-10

Family

ID=27741145

Family Applications (2)

Application Number Title Priority Date Filing Date
EP02005137A Withdrawn EP1342953A1 (fr) 2002-03-07 2002-03-07 Turbine à gaz
EP03706564A Expired - Fee Related EP1483536B1 (fr) 2002-03-07 2003-02-24 Turbine a gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP03706564A Expired - Fee Related EP1483536B1 (fr) 2002-03-07 2003-02-24 Turbine a gaz

Country Status (7)

Country Link
US (1) US7246493B2 (fr)
EP (2) EP1342953A1 (fr)
JP (1) JP4429730B2 (fr)
CN (1) CN1320314C (fr)
DE (1) DE50309686D1 (fr)
ES (1) ES2303892T3 (fr)
WO (1) WO2003074936A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005003634A1 (fr) * 2003-07-04 2005-01-13 Siemens Aktiengesellschaft Unite de combustion pour turbine a gaz et turbine a gaz
WO2006082210A1 (fr) * 2005-02-04 2006-08-10 Enel Produzione S.P.A. Reduction d’oscillation thermoacoustique dans des chambres de combustion de turbine a gaz avec plenum annulaire
EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
ITMI20122265A1 (it) * 2012-12-28 2014-06-29 Ansaldo Energia Spa Gruppo bruciatore per una turbina a gas provvisto di risonatore di helmholtz
WO2015189101A1 (fr) * 2014-06-13 2015-12-17 Siemens Aktiengesellschaft Système de brûleur avec résonateur
DE102005062284B4 (de) * 2005-12-24 2019-02-28 Ansaldo Energia Ip Uk Limited Brennkammer für eine Gasturbine

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7272931B2 (en) * 2003-09-16 2007-09-25 General Electric Company Method and apparatus to decrease combustor acoustics
EP1645805A1 (fr) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft brûleur pour combustible fluide et procédé pour uriliser un tel brûleur
US7788926B2 (en) * 2006-08-18 2010-09-07 Siemens Energy, Inc. Resonator device at junction of combustor and combustion chamber
KR101201559B1 (ko) 2007-11-21 2012-11-14 미츠비시 쥬고교 가부시키가이샤 감쇠 장치 및 가스 터빈 연소기
US8516819B2 (en) 2008-07-16 2013-08-27 Siemens Energy, Inc. Forward-section resonator for high frequency dynamic damping
CH699322A1 (de) * 2008-08-14 2010-02-15 Alstom Technology Ltd Verfahren zum einstellen eines helmholtz-resonators sowie helmholtz-resonator zur durchführung des verfahrens.
US8336312B2 (en) * 2009-06-17 2012-12-25 Siemens Energy, Inc. Attenuation of combustion dynamics using a Herschel-Quincke filter
US8789372B2 (en) * 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator
US8474265B2 (en) * 2009-07-29 2013-07-02 General Electric Company Fuel nozzle for a turbine combustor, and methods of forming same
US20110209481A1 (en) * 2010-02-26 2011-09-01 General Electric Company Turbine Combustor End Cover
EP2383515B1 (fr) 2010-04-28 2013-06-19 Siemens Aktiengesellschaft Système de brûleur pour l'amortissement d'un tel système de brûleur
EP2383514A1 (fr) 2010-04-28 2011-11-02 Siemens Aktiengesellschaft Système de brûleur et procédé d'amortissement d'un tel système de brûleur
US9810081B2 (en) 2010-06-11 2017-11-07 Siemens Energy, Inc. Cooled conduit for conveying combustion gases
US8720204B2 (en) 2011-02-09 2014-05-13 Siemens Energy, Inc. Resonator system with enhanced combustor liner cooling
EP2642203A1 (fr) * 2012-03-20 2013-09-25 Alstom Technology Ltd Amortisseur de helmholtz annulaire
US9188342B2 (en) * 2012-03-21 2015-11-17 General Electric Company Systems and methods for dampening combustor dynamics in a micromixer
JP6456481B2 (ja) 2014-08-26 2019-01-23 シーメンス エナジー インコーポレイテッド ガスタービンエンジン内の音響共鳴器用のフィルム冷却孔配列
CN104595928B (zh) * 2015-01-23 2020-02-14 北京华清燃气轮机与煤气化联合循环工程技术有限公司 扩散燃烧室声学火焰筒
JP2020056542A (ja) * 2018-10-02 2020-04-09 川崎重工業株式会社 航空機用のアニュラ型ガスタービン燃焼器

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4122674A (en) * 1976-12-27 1978-10-31 The Boeing Company Apparatus for suppressing combustion noise within gas turbine engines
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
EP0577862A1 (fr) * 1992-07-03 1994-01-12 Abb Research Ltd. Dispositif de post-combustion
EP0597138A1 (fr) 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
US5644918A (en) * 1994-11-14 1997-07-08 General Electric Company Dynamics free low emissions gas turbine combustor
EP0971172A1 (fr) * 1998-07-10 2000-01-12 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
US6058709A (en) 1996-11-06 2000-05-09 The United States Of America Represented By The United States Department Of Energy Dynamically balanced fuel nozzle and method of operation
EP1004823A2 (fr) 1998-11-10 2000-05-31 Asea Brown Boveri AG Dispositif d'amortissement pour la réduction de l'amplitude d'oscillation d'ondes acoustiques pour un brûleur
EP1158247A2 (fr) * 2000-05-26 2001-11-28 ALSTOM Power N.V. Dispositif pour la réduction des vibrations accoustiques dans une chambre de combustion

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US3819009A (en) * 1973-02-01 1974-06-25 Gen Electric Duct wall acoustic treatment
US4231447A (en) * 1978-04-29 1980-11-04 Rolls-Royce Limited Multi-layer acoustic linings
DE3241162A1 (de) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner
JP3183053B2 (ja) * 1994-07-20 2001-07-03 株式会社日立製作所 ガスタービン燃焼器及びガスタービン
EP0918190A1 (fr) * 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6374593B1 (en) * 1998-03-20 2002-04-23 Siemens Aktiengesellschaft Burner and method for reducing combustion humming during operation
DE19839085C2 (de) * 1998-08-27 2000-06-08 Siemens Ag Brenneranordnung mit primärem und sekundärem Pilotbrenner
DE59810760D1 (de) * 1998-12-15 2004-03-18 Krasnojarskij Politekhn I Kras Brennkammer mit akustisch gedämpftem Brennstoffversorgungssystem
US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
GB2390150A (en) * 2002-06-26 2003-12-31 Alstom Reheat combustion system for a gas turbine including an accoustic screen

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4122674A (en) * 1976-12-27 1978-10-31 The Boeing Company Apparatus for suppressing combustion noise within gas turbine engines
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
EP0577862A1 (fr) * 1992-07-03 1994-01-12 Abb Research Ltd. Dispositif de post-combustion
EP0597138A1 (fr) 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
US5644918A (en) * 1994-11-14 1997-07-08 General Electric Company Dynamics free low emissions gas turbine combustor
US6058709A (en) 1996-11-06 2000-05-09 The United States Of America Represented By The United States Department Of Energy Dynamically balanced fuel nozzle and method of operation
EP0971172A1 (fr) * 1998-07-10 2000-01-12 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
EP1004823A2 (fr) 1998-11-10 2000-05-31 Asea Brown Boveri AG Dispositif d'amortissement pour la réduction de l'amplitude d'oscillation d'ondes acoustiques pour un brûleur
EP1158247A2 (fr) * 2000-05-26 2001-11-28 ALSTOM Power N.V. Dispositif pour la réduction des vibrations accoustiques dans une chambre de combustion

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005003634A1 (fr) * 2003-07-04 2005-01-13 Siemens Aktiengesellschaft Unite de combustion pour turbine a gaz et turbine a gaz
WO2006082210A1 (fr) * 2005-02-04 2006-08-10 Enel Produzione S.P.A. Reduction d’oscillation thermoacoustique dans des chambres de combustion de turbine a gaz avec plenum annulaire
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
DE102005062284B4 (de) * 2005-12-24 2019-02-28 Ansaldo Energia Ip Uk Limited Brennkammer für eine Gasturbine
EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
ITMI20122265A1 (it) * 2012-12-28 2014-06-29 Ansaldo Energia Spa Gruppo bruciatore per una turbina a gas provvisto di risonatore di helmholtz
WO2014102749A1 (fr) * 2012-12-28 2014-07-03 Ansaldo Energia S.P.A. Ensemble de brûleur de turbine à gaz comportant un résonateur d'helmholtz
CN105121961B (zh) * 2012-12-28 2017-05-31 安萨尔多能源公司 配备有亥姆霍兹共振器的燃气涡轮机燃烧器组件
WO2015189101A1 (fr) * 2014-06-13 2015-12-17 Siemens Aktiengesellschaft Système de brûleur avec résonateur

Also Published As

Publication number Publication date
EP1483536A1 (fr) 2004-12-08
JP4429730B2 (ja) 2010-03-10
EP1483536B1 (fr) 2008-04-23
CN1639512A (zh) 2005-07-13
US20050144950A1 (en) 2005-07-07
WO2003074936A1 (fr) 2003-09-12
DE50309686D1 (de) 2008-06-05
US7246493B2 (en) 2007-07-24
CN1320314C (zh) 2007-06-06
JP2005527763A (ja) 2005-09-15
ES2303892T3 (es) 2008-09-01

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