EP1235033B1 - Chambre de combustion annulaire et méthode d'opération de la dite chambre - Google Patents

Chambre de combustion annulaire et méthode d'opération de la dite chambre Download PDF

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Publication number
EP1235033B1
EP1235033B1 EP02405087A EP02405087A EP1235033B1 EP 1235033 B1 EP1235033 B1 EP 1235033B1 EP 02405087 A EP02405087 A EP 02405087A EP 02405087 A EP02405087 A EP 02405087A EP 1235033 B1 EP1235033 B1 EP 1235033B1
Authority
EP
European Patent Office
Prior art keywords
premix
combustion chamber
annular combustion
burners
burner
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.)
Expired - Lifetime
Application number
EP02405087A
Other languages
German (de)
English (en)
Other versions
EP1235033A3 (fr
EP1235033A2 (fr
Inventor
Klaus Dr. Döbbeling
Hans Peter Knöpfel
Christian Oliver Dr. Paschereit
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
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1235033A2 publication Critical patent/EP1235033A2/fr
Publication of EP1235033A3 publication Critical patent/EP1235033A3/fr
Application granted granted Critical
Publication of EP1235033B1 publication Critical patent/EP1235033B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement
    • 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 method for operating an annular combustion chamber and to an annular combustion chamber with a plurality of circularly arranged premix burners, in each of which a fuel-air mixture is generated before it is brought to ignition and used as a hot gas stream for driving at least one turbine stage of a gas turbine plant ,
  • premix combustion When burning liquid or gaseous fuel in a combustion chamber of a gas turbine, so-called premix combustion has become established.
  • the fuel and the combustion air are mixed as uniformly as possible and then passed into the combustion chamber.
  • annular combustion chambers which provides a plurality of individual Vormischhbrenner in a circular arrangement around the rotating components of a gas turbine and their hot gases over a ring-shaped flow channel can be supplied directly to the downstream turbine stage.
  • a related Ringbrennkamer premix burners for a gas turbine is for example from the EP-B1-597 138 known.
  • the premix burners provided at the top end of the annular combustion chamber are known, for example, from US Pat EP-A1-387 532 known.
  • Such premix burners are so-called double-cone burners.
  • this type of premix burner consists of two hollow, conical body parts, which are nested in the flow direction. The respective central axes of the two body parts are offset from each other. The adjacent walls of the two body parts form in their longitudinal extent tangential slots for the combustion air, which passes in this way into the burner interior.
  • a fuel nozzle for liquid fuel is arranged. The fuel is injected at an acute angle into the hollow cone. The resulting conical liquid fuel profile is enclosed by the tangential incoming combustion air. In the axial direction, the concentration of the fuel is continuously reduced as a result of mixing with the combustion air.
  • the premix burner can also be operated with gaseous fuel.
  • gaseous fuel for this purpose, in the region of the tangential slots in the walls of the two partial bodies distributed in the longitudinal direction Gaseinströmö Samuelen, the so-called Premixbelochung provided.
  • the mixture formation with the combustion air thus begins already in the zone of the inlet slots. It is understood that in this way a mixed operation with both types of fuel is possible.
  • the most homogeneous possible fuel concentration is established over the applied annular cross-section. The result is a defined dome-shaped remindströmzone at the burner outlet at the top of the ignition.
  • the fuel distribution ie the mixture profile of the fuel / air mixture in the area of flame stabilization also plays a major role.
  • the mixing profile between fuel and air within the premix burner is determined by the premixing pattern, ie the spatial arrangement of the apertures typically distributed along the air inlet slots, through which premix fuel, preferably premix gas, is injected into the premix burner.
  • US 5 482 457 A describes a premix burner with a premix gas puff, with adjacent openings at a different distance from one another.
  • the invention is based on the object, a method for operating an annular combustion chamber and a related annular combustion chamber with a plurality of circularly arranged premix burners, in each of which a fuel-air mixture is generated before it brought to ignition and as a hot gas flow to drive at least one turbine stage of a gas turbine plant is used in such a way, that the above-mentioned disadvantages should be avoided.
  • measures should be taken that decisively counteract the combustion chamber pulsations that occur.
  • the burnout is to be completed and the occurring CO, UHC, NO x emissions reduced.
  • a method for operating a combustion chamber with a plurality of circularly arranged premix burners according to the preamble of claim 5 is designed such that the at least one premix burner generates a different from all other premix burners of the annular combustion chamber spatial mixing profile within the fuel-air mixture.
  • an annular combustion chamber according to the preamble of claim 1, characterized in that at least one premix burner within the annular combustion chamber having a deviating from all other premix burners Premixgasbelochung with at least one area in the adjacent openings of the Premixgasbelochung a different distance from each other have remaining region of the Premixgasbelochung, while all other premix burners within the annular combustion chamber have a uniformly distributed Premixgasbelochung.
  • the idea underlying the invention is based on the targeted breaking of the symmetry, which is structurally predetermined by the circular arrangement of a plurality of identically designed premix burners around the rotating components of a gas turbine plant. Since typically identical premix burners are arranged in a ring around the rotating components of the gas turbine plant, which each form identical mixing profiles within the individual fuel-air mixtures due to their identical design - this is the result of identical premixing pebbles -, the annular combustion chamber is formed in certain load ranges Circular rotating, pulsating waves that need to be specifically suppressed.
  • Fig. 1 is a longitudinal section along the line II in the FIG. 2 represented by two adjacent premix burners 1, 2, which are arranged side by side on an annular peripheral front plate 3 of an annular combustion chamber 13.
  • a schematic view along the line II-II in the FIG. 1 on the annular combustion chamber 13 is in the FIG. 2 visible, noticeable.
  • the cone-shaped premix burners 1, 2 have an outlet opening 4, 5, which open downstream into the combustion chamber 6.
  • the premix burners 1, 2 have along their air inlet slots 7, 8 a premix fuel purging 9, which consists of individual openings through which preferably gaseous fuel 10 into the interior of the cone-shaped premix burner 1, 2 opens.
  • the spatial distribution of the Premixgasbelochung 9 of the premix burner 1 is homogeneously distributed in a conventional manner, i. the Premixgaslöcher are arranged equidistant from each other. With such a Premixbelochungspattern a spatially uniformly distributed, homogeneous mixture profile 11 is usually achieved over the entire cross section of the outlet opening 4.
  • the premix burner 2 has two regions along the premixing pattern, in which the individual premix gas holes 9 have different distances from each other.
  • the premix burner 2 in which the downstream Premixlöcher have a greater mutual distance than upstream, we obtain a mixture profile 12, which is designed in the manner of a Gauss distribution.
  • At least three premix burners 2 should be formed in the above manner for effective prevention of said pulsations within the combustion chamber and circularly distributed uniformly around the annular combustion chamber 13.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Claims (6)

  1. Chambre de combustion annulaire (13) pour produire un gaz chaud pour l'entraînement d'une turbine à gaz comprenant une pluralité de brûleurs à prémélange (1, 2) disposés en cercle avec un système d'ouvertures à gaz de prémélange (9) à l'intérieur du brûleur à prémélange (1, 2),
    caractérisée en ce que
    au moins un brûleur à prémélange (2) présente, à l'intérieur de la chambre de combustion annulaire (13), un système d'ouvertures à gaz de prémélange (9) différent de tous les autres brûleurs à prémélange (1) avec au moins une région dans laquelle des ouvertures adjacentes du système d'ouvertures à gaz de prémélange (9) présentent une distance différente les unes par rapport aux autres, par rapport au reste de la région du système d'ouvertures à gaz de prémélange (9), tandis que tous les autres brûleurs à prémélange (1) à l'intérieur de la chambre annulaire (13) présentent un système d'ouvertures à gaz de prémélange (9) équidistantes.
  2. Chambre de combustion annulaire (13) selon la revendication 1,
    caractérisée en ce que
    dans le cas de l'au moins un brûleur à prémélange (2) à l'intérieur du brûleur à prémélange (2), les ouvertures du système d'ouvertures à gaz de prémélange (9) disposées en aval présentent une distance mutuelle plus grande que les ouvertures en amont.
  3. Chambre de combustion annulaire (13) selon la revendication 1,
    caractérisée en ce que
    dans le cas de l'au moins un brûleur à prémélange (2), à l'intérieur du brûleur à prémélange (2), les ouvertures du système d'ouvertures à gaz de prémélange (9) disposées en amont présentent une plus grande distance mutuelle que les ouvertures en aval.
  4. Chambre de combustion annulaire (13) selon la revendication 1,
    caractérisée en ce que
    au moins trois brûleurs à prémélange sont réalisés de la manière décrite ci-dessus et en ce que les au moins trois brûleurs à prémélange sont répartis uniformément en cercle autour de la chambre de combustion annulaire (13).
  5. Procédé pour faire fonctionner une chambre de combustion annulaire (13) selon la revendication 1,
    caractérisé en ce que
    l'au moins un brûleur à prémélange (2) produit à l'intérieur du mélange air-combustible un profil de mélange (12) spatial s'écartant de tous les autres brûleurs à prémélange (1) de la chambre de combustion annulaire (13).
  6. Procédé selon la revendication 5,
    caractérisé en ce
    qu'au moins trois brûleurs à prémélange (2) fonctionnent de telle sorte que ces au moins trois brûleurs à prémélange (2) présentent à l'intérieur du mélange air-combustible un profil de mélange (12) spatial s'écartant de tous les autres brûleurs à prémélange (1) de la chambre de combustion annulaire (13).
EP02405087A 2001-02-22 2002-02-07 Chambre de combustion annulaire et méthode d'opération de la dite chambre Expired - Lifetime EP1235033B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10108560 2001-02-22
DE10108560A DE10108560A1 (de) 2001-02-22 2001-02-22 Verfahren zum Betrieb einer Ringbrennkammer sowie eine diesbezügliche Ringbrennkammer

Publications (3)

Publication Number Publication Date
EP1235033A2 EP1235033A2 (fr) 2002-08-28
EP1235033A3 EP1235033A3 (fr) 2003-10-08
EP1235033B1 true EP1235033B1 (fr) 2009-04-01

Family

ID=7675131

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02405087A Expired - Lifetime EP1235033B1 (fr) 2001-02-22 2002-02-07 Chambre de combustion annulaire et méthode d'opération de la dite chambre

Country Status (4)

Country Link
US (1) US6691518B2 (fr)
EP (1) EP1235033B1 (fr)
JP (1) JP2002257346A (fr)
DE (2) DE10108560A1 (fr)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1394471A1 (fr) 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Brûleur
DE60228085D1 (de) * 2002-09-20 2008-09-18 Siemens Ag Vormischbrenner mit profilierter Luftmassenströmung
DE10325455A1 (de) * 2003-06-05 2004-12-30 Alstom Technology Ltd Verfahren zum Betrieb einer ringförmigen Brenneranordnung in einer Zwischenerhitzungsstufe einer mehrstufigen Verbrennungseinrichtung einer Gasturbine
US7506511B2 (en) * 2003-12-23 2009-03-24 Honeywell International Inc. Reduced exhaust emissions gas turbine engine combustor
EP1730448B1 (fr) * 2004-03-31 2016-12-14 General Electric Technology GmbH Ensemble a plusieurs bruleurs servant a faire fonctionner une chambre de combustion et procede pour faire fonctionner un tel ensemble
WO2005095863A1 (fr) * 2004-03-31 2005-10-13 Alstom Technology Ltd Brûleur
DE102004049491A1 (de) * 2004-10-11 2006-04-20 Alstom Technology Ltd Vormischbrenner
EP1828684A1 (fr) * 2004-12-23 2007-09-05 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange
US20070089427A1 (en) * 2005-10-24 2007-04-26 Thomas Scarinci Two-branch mixing passage and method to control combustor pulsations
US7805922B2 (en) * 2006-02-09 2010-10-05 Siemens Energy, Inc. Fuel flow tuning for a stage of a gas turbine engine
EP2119964B1 (fr) * 2008-05-15 2018-10-31 Ansaldo Energia IP UK Limited Procédé pour réduire les émissions d'une chambre à combustion
US8616003B2 (en) 2008-07-21 2013-12-31 Parker-Hannifin Corporation Nozzle assembly
IT1391245B1 (it) * 2008-08-08 2011-12-01 Ansaldo Energia Spa Metodo per determinare la collocazione di bruciatori in una camera di combustione anulare di una turbina a gas
JP5462502B2 (ja) * 2009-03-06 2014-04-02 大阪瓦斯株式会社 管状火炎バーナ
EP2423589A1 (fr) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Agencement de brûleur
JP2019020071A (ja) * 2017-07-19 2019-02-07 三菱重工業株式会社 燃焼器及びガスタービン
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

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US3010281A (en) * 1957-12-24 1961-11-28 Adolph J Cervenka Toroidal combustion chamber
CH678757A5 (fr) * 1989-03-15 1991-10-31 Asea Brown Boveri
EP0481111B1 (fr) * 1990-10-17 1995-06-28 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
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
FR2694799B1 (fr) * 1992-08-12 1994-09-23 Snecma Chambre de combustion annulaire conventionnelle à plusieurs injecteurs.
DE59209209D1 (de) * 1992-10-16 1998-04-02 Asea Brown Boveri Gasbetriebener Vormischbrenner
EP0597138B1 (fr) 1992-11-09 1997-07-16 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz
JPH06272862A (ja) * 1993-03-18 1994-09-27 Hitachi Ltd 燃料空気混合方法およびその混合装置
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DE4411622A1 (de) * 1994-04-02 1995-10-05 Abb Management Ag Vormischbrenner
US5687571A (en) * 1995-02-20 1997-11-18 Asea Brown Boveri Ag Combustion chamber with two-stage combustion
DE19510744A1 (de) * 1995-03-24 1996-09-26 Abb Management Ag Brennkammer mit Zweistufenverbrennung
EP0747635B1 (fr) * 1995-06-05 2003-01-15 Rolls-Royce Corporation Brûleur à prémélange pauvre avec faible production de NOx pour turbines à gaz industrielles
DE19615910B4 (de) * 1996-04-22 2006-09-14 Alstom Brenneranordnung
EP0976982B1 (fr) * 1998-07-27 2003-12-03 ALSTOM (Switzerland) Ltd Procédé de fonctionnement d'une chambre de combustion de turbine à gaz à carburant liquide
DE19939235B4 (de) * 1999-08-18 2012-03-29 Alstom Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens

Also Published As

Publication number Publication date
US20020134086A1 (en) 2002-09-26
JP2002257346A (ja) 2002-09-11
DE50213404D1 (de) 2009-05-14
DE10108560A1 (de) 2002-09-05
EP1235033A3 (fr) 2003-10-08
US6691518B2 (en) 2004-02-17
EP1235033A2 (fr) 2002-08-28

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