EP2423589A1 - Agencement de brûleur - Google Patents

Agencement de brûleur Download PDF

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Publication number
EP2423589A1
EP2423589A1 EP10174338A EP10174338A EP2423589A1 EP 2423589 A1 EP2423589 A1 EP 2423589A1 EP 10174338 A EP10174338 A EP 10174338A EP 10174338 A EP10174338 A EP 10174338A EP 2423589 A1 EP2423589 A1 EP 2423589A1
Authority
EP
European Patent Office
Prior art keywords
burners
fuel
burner
arrangement according
burner arrangement
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Withdrawn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
EP10174338A
Other languages
German (de)
English (en)
Inventor
Matthias Hase
Jürgen MEISL
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 EP10174338A priority Critical patent/EP2423589A1/fr
Priority to US13/819,351 priority patent/US20130180251A1/en
Priority to PCT/EP2011/064072 priority patent/WO2012025427A1/fr
Priority to EP11745767.1A priority patent/EP2609368A1/fr
Priority to JP2013525249A priority patent/JP5606628B2/ja
Publication of EP2423589A1 publication Critical patent/EP2423589A1/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Withdrawn legal-status Critical Current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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F23C5/08—Disposition of burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/12—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23R3/28—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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/06042—Annular arrangement of burners in a furnace, e.g. in a gas turbine, operated in alternate lean-rich mode
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11002—Liquid fuel burners with more than one nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to a burner assembly according to the preamble of claim 1.
  • the combustion chamber is supplied with compressed air from the compressor.
  • the compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber.
  • the hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.
  • a burner assembly has a carrier with at least two burners, which are mounted in the flow direction on the carrier.
  • Each burner comprises a cylindrical housing with a centrally disposed, a fuel channel having lance, which is supported via swirl vanes on the housing.
  • an attachment is arranged on the side leading to a combustion chamber, wherein at least one fuel nozzle in the attachment is preferably arranged downstream of the swirl blades and connected to the fuel channel.
  • gas turbines especially those that are operated with two different fuels, for example, an injection of the fuel oil in the range of swirl generators, in which the oil is mixed with air. For better mixing of oil and air, the oil within the nozzles used for the injection into a swirling motion is added. This oil nozzle is also referred to as a pressure-swirl nozzle.
  • the oil nozzles can not be arranged so that the mixing of the fuel with the air leads to an optimal result in terms of pressure pulsations.
  • the object of the present invention is therefore to provide a burner assembly which solves the above problem.
  • the at least two fuel nozzles of the at least two burners have a different functional characteristic and / or spray form.
  • a smearing By such a smearing, one understands effects such as e.g. Broadening of the flame zone, avoiding symmetrical structures and creating zones with different temperatures. This leads to an improved thermoacoustic behavior.
  • Fig. 1 shows a single burner 2 of such a burner assembly according to the invention.
  • swirl blades 4 are arranged around a lance.
  • the swirl blades 4 are arranged along the circumference of the lance in the housing 12.
  • a compressor air flow 7 in the leading to a combustion chamber (not shown) leading part of the burner 2 is passed.
  • the air is displaced by the swirl blades 4 in a swirling motion.
  • the lance also comprises a fuel channel 3.
  • the burner 2 further comprises an attachment 10 on the side leading to the combustion chamber.
  • the attachment 10 can be welded, screwed or directly cast with the lance, for example.
  • the mostly multiple fuel nozzles 1 are arranged in the attachment 10 preferably downstream of the swirl vanes 4 and are fluidically connected to the fuel passage 3, here represented as an oil passage.
  • the fuel passage 3 here represented as an oil passage.
  • eight such burners 2 are arranged circularly on a support (not shown).
  • the burners 2 are arranged around a pilot burner (not shown) with pilot cone.
  • the swirl blades 4 and additional fuel nozzles which are not shown here, however, have.
  • the at least two burners 2 have fuel nozzles 1 according to the invention, each with different functional characteristics and / or spray form. This means that the fuel nozzles 1 of the one burner 2 differ from the fuel nozzles 1 of the other burner 2 with regard to their functional characteristics and / or their spray form.
  • three or more burners 2 may have fuel nozzles 1 according to the invention with a respectively different functional characteristic and / or spray shape. The number of burners 2 and the number of fuel nozzles 1, each with different functional characteristics and / or spray shape is therefore not fixed.
  • the functional characteristic of a fuel nozzle 1 is characterized at least by the nozzle size, the jet angle, the liquid distribution and the Zerstäubungs characterizing.
  • the nozzle size essentially determines the fuel mass flow at a given pressure difference.
  • the atomization characteristic comprises at least the droplet size distribution.
  • simple pressure atomizers, swirl nozzles, or air-protected atomizers can be used. It is also possible to distinguish between the spray form, so that the fuel nozzles 1 can, for example, form a full jet, hollow cone jet, a full cone jet or a flat jet. Other spray forms are possible.
  • the fuel nozzles 1 of the respective burners 2 have a different distribution and penetration behavior of the fuel into the compressor air flow 7 due to the different functional characteristics and / or spray form. For example, a significantly wider penetration of the fuel into the airflow 7 may result in a narrower distribution of the fuel around the periphery of the attachment 10.
  • the different distribution and penetration behavior leads to a different stabilization of the flame zone of the respective burners 2. This results in a smearing of the combustion zones in the entire combustion system. The amount of energy available for feedback at a given frequency is thus reduced and falls below a critical limit. This leads to an improved thermoacoustic behavior.
  • Fig. 2 shows a fuel distribution of a first burner assembly according to the invention with eight burners 2a, 2b from the front.
  • the invention is not limited to eight burners 2a, 2b and a different number of burners is possible.
  • the burner 2a fuel nozzles 1 ( Fig.1 ) having a function characteristic and spray shape which cause a mean radial penetration depth and a wide fuel distribution around the attachment 10.
  • the burner 2a therefore has a wide fuel distribution ring 19a the essay 10 around.
  • the fuel distribution ring 19a has a large radial distance from the attachment 10.
  • the burners 2b have fuel nozzles 1 (FIG. Fig. 1 ) with a functional characteristic and spray shape, which cause a very small radial penetration depth and a narrow fuel distribution around the attachment 10 around.
  • the burner 2b therefore has a narrow fuel distribution ring 19b around the attachment 10 around.
  • the fuel distribution ring 19b also has a small radial distance from the attachment 10.
  • Fig. 2 shows a symmetrical arrangement of burners 2a, 2b.
  • the four burners 2a are arranged opposite each other with the same functional characteristics and spray form. This also applies to the burner 2b. However, other arrangements may be possible.
  • Fig. 3 shows a fuel distribution of a second burner assembly according to the invention with eight burners 2a, 2b from the front.
  • the burners 2a, 2b are arranged alternately.
  • Burner arrangements are shown which each have two burners 2a, 2b with a different functional characteristic and / or spray form in the fuel nozzles 1 (FIG. Fig. 1 ) exhibit. However, it is also possible to use a plurality of burners 2 with different functional characteristics and / or spray form in the fuel nozzles 1 (FIG. Fig. 1 ) may be present in such a burner arrangement.
  • Fig. 4 shows a fuel distribution of a third burner assembly according to the invention with eight burners 2a, 2b from the front.
  • Six burners 2a have fuel nozzles 1 (FIG. Fig. 1 ) with the same functional characteristics and spray shape
  • the two other burners 2b have fuel nozzles 1 ( Fig. 1 ) with a different functional characteristics and / or spray shape.
  • the function characteristic and spray shape of the fuel nozzles 1 of the burner 2b is equal to each other. This corresponds to an asymmetrical arrangement of burners 2a, 2b. Under thermoacoustic In view of such an asymmetrical arrangement is particularly advantageous to prevent circumferential modes in the entire burner system.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP10174338A 2010-08-27 2010-08-27 Agencement de brûleur Withdrawn EP2423589A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP10174338A EP2423589A1 (fr) 2010-08-27 2010-08-27 Agencement de brûleur
US13/819,351 US20130180251A1 (en) 2010-08-27 2011-08-16 Burner arrangement
PCT/EP2011/064072 WO2012025427A1 (fr) 2010-08-27 2011-08-16 Ensemble brûleur
EP11745767.1A EP2609368A1 (fr) 2010-08-27 2011-08-16 Ensemble brûleur
JP2013525249A JP5606628B2 (ja) 2010-08-27 2011-08-16 バーナ装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10174338A EP2423589A1 (fr) 2010-08-27 2010-08-27 Agencement de brûleur

Publications (1)

Publication Number Publication Date
EP2423589A1 true EP2423589A1 (fr) 2012-02-29

Family

ID=43479478

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10174338A Withdrawn EP2423589A1 (fr) 2010-08-27 2010-08-27 Agencement de brûleur
EP11745767.1A Ceased EP2609368A1 (fr) 2010-08-27 2011-08-16 Ensemble brûleur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11745767.1A Ceased EP2609368A1 (fr) 2010-08-27 2011-08-16 Ensemble brûleur

Country Status (4)

Country Link
US (1) US20130180251A1 (fr)
EP (2) EP2423589A1 (fr)
JP (1) JP5606628B2 (fr)
WO (1) WO2012025427A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016038016A1 (fr) * 2014-09-12 2016-03-17 Siemens Aktiengesellschaft Brûleur pour une turbine à gaz et turbine à gaz
CN110056863A (zh) * 2019-04-30 2019-07-26 恩平市景业陶瓷有限公司 一种用于煤焦油的燃烧装置

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5458121B2 (ja) * 2012-01-27 2014-04-02 株式会社日立製作所 ガスタービン燃焼器およびガスタービン燃焼器の運転方法
JP6021705B2 (ja) * 2013-03-22 2016-11-09 三菱重工業株式会社 燃焼器、および、ガスタービン
JP5984770B2 (ja) 2013-09-27 2016-09-06 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器およびこれを備えたガスタービン機関
EP3204694B1 (fr) 2014-10-06 2019-02-27 Siemens Aktiengesellschaft Chambre de combustion et procédé d'amortissement de modes vibratoires sous une dynamique de combustion à haute fréquence
US20190056108A1 (en) * 2017-08-21 2019-02-21 General Electric Company Non-uniform mixer for combustion dynamics attenuation

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DE19615910A1 (de) * 1996-04-22 1997-10-23 Asea Brown Boveri Brenneranordnung
DE19939235A1 (de) * 1999-08-18 2001-02-22 Asea Brown Boveri Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
US6269646B1 (en) * 1998-01-28 2001-08-07 General Electric Company Combustors with improved dynamics
EP1235033A2 (fr) * 2001-02-22 2002-08-28 ALSTOM (Switzerland) Ltd Chambre de combustion annulaire et méthode d'opération de la dite chambre
US20040093851A1 (en) * 2002-11-19 2004-05-20 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
GB2454247A (en) * 2007-11-02 2009-05-06 Siemens Ag A Combustor for a Gas-Turbine Engine Has a Burner Head with Fuel Delivered at a Compound Angle

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JPH05203148A (ja) * 1992-01-13 1993-08-10 Hitachi Ltd ガスタービン燃焼装置及びその制御方法
US5309710A (en) * 1992-11-20 1994-05-10 General Electric Company Gas turbine combustor having poppet valves for air distribution control
EP0925472B1 (fr) * 1996-09-16 2001-04-04 Siemens Aktiengesellschaft Procede pour la suppression des oscillations de combustion et dispositif pour la combustion d'un combustible avec de l'air
DE59704739D1 (de) * 1996-12-20 2001-10-31 Siemens Ag Brenner für fluidische brennstoffe
ATE234444T1 (de) * 1997-10-27 2003-03-15 Alstom Switzerland Ltd Verfahren zum betrieb eines vormischbrenners
JP2002517700A (ja) * 1998-06-04 2002-06-18 シーメンス アクチエンゲゼルシヤフト 燃料噴射ノズル
WO2000012940A1 (fr) * 1998-08-31 2000-03-09 Siemens Aktiengesellschaft Procede d'exploitation d'une turbine a gaz et turbine a gaz correspondante
JP2001280641A (ja) * 2000-03-31 2001-10-10 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器、および、ガスタービン燃焼器における燃料と空気の混合方法
US6539724B2 (en) * 2001-03-30 2003-04-01 Delavan Inc Airblast fuel atomization system
JP3498142B2 (ja) * 2001-08-01 2004-02-16 独立行政法人航空宇宙技術研究所 壁面衝突式液体微粒化ノズル
JP2003090535A (ja) * 2001-09-17 2003-03-28 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンの燃焼器
JP2005288390A (ja) * 2004-04-02 2005-10-20 Kyoritsu Gokin Co Ltd 二流体ノズル及び噴霧方法
US7827797B2 (en) * 2006-09-05 2010-11-09 General Electric Company Injection assembly for a combustor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19615910A1 (de) * 1996-04-22 1997-10-23 Asea Brown Boveri Brenneranordnung
US6269646B1 (en) * 1998-01-28 2001-08-07 General Electric Company Combustors with improved dynamics
DE19939235A1 (de) * 1999-08-18 2001-02-22 Asea Brown Boveri Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
EP1235033A2 (fr) * 2001-02-22 2002-08-28 ALSTOM (Switzerland) Ltd Chambre de combustion annulaire et méthode d'opération de la dite chambre
US20040093851A1 (en) * 2002-11-19 2004-05-20 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
GB2454247A (en) * 2007-11-02 2009-05-06 Siemens Ag A Combustor for a Gas-Turbine Engine Has a Burner Head with Fuel Delivered at a Compound Angle

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016038016A1 (fr) * 2014-09-12 2016-03-17 Siemens Aktiengesellschaft Brûleur pour une turbine à gaz et turbine à gaz
CN110056863A (zh) * 2019-04-30 2019-07-26 恩平市景业陶瓷有限公司 一种用于煤焦油的燃烧装置

Also Published As

Publication number Publication date
US20130180251A1 (en) 2013-07-18
JP2013536397A (ja) 2013-09-19
EP2609368A1 (fr) 2013-07-03
WO2012025427A1 (fr) 2012-03-01
JP5606628B2 (ja) 2014-10-15

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