EP2260238B1 - Procédé de fonctionnement d'un brûleur à prémélange - Google Patents

Procédé de fonctionnement d'un brûleur à prémélange Download PDF

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Publication number
EP2260238B1
EP2260238B1 EP09717497.3A EP09717497A EP2260238B1 EP 2260238 B1 EP2260238 B1 EP 2260238B1 EP 09717497 A EP09717497 A EP 09717497A EP 2260238 B1 EP2260238 B1 EP 2260238B1
Authority
EP
European Patent Office
Prior art keywords
fuel
mixing pipe
premix burner
section
swirl generator
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.)
Not-in-force
Application number
EP09717497.3A
Other languages
German (de)
English (en)
Other versions
EP2260238A1 (fr
Inventor
Richard Carroni
Alexander Ni
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
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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2260238A1 publication Critical patent/EP2260238A1/fr
Application granted granted Critical
Publication of EP2260238B1 publication Critical patent/EP2260238B1/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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • 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
    • 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
    • F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel

Definitions

  • the present invention relates to the field of combustion technology. It relates to a method for operating a premix burner according to the preamble of claim 1.
  • Fig. 1 along a burner axis 15 comprise a premix burner 11 producing an air / fuel mixture 12 in the form of a double-cone burner and a subsequent mixing tube 13 opening into a combustion chamber 14 ( EP-A2-0 704 657 . EP-A1-0 913 630 . US-A-6,045,351 . WO-A1-2006 / 069861 DE-A1-4417538 . EP-A2-0694740 . EP-A2-1207350 ).
  • Essential for the invention is a mixing tube which has a constriction, wherein at the height of the constriction means are provided for the injection of highly reactive, in particular H2-rich fuel.
  • the constriction (as constriction) can be moved upstream.
  • the highly reactive fuel is then injected directly at the bottleneck.
  • An embodiment of the invention is characterized in that the mixing tube tapers conically in a first mixing pipe section from the swirl generator to constriction, and that the mixing tube in a second mixing pipe section from the constriction to the combustion chamber in diameter significantly smaller than at the output of the swirl generator Case is ..
  • the second mixing pipe section starting at the constriction can have a constant diameter up to the combustion chamber.
  • the second mixing pipe section can also be slightly conical up to the combustion chamber.
  • the means for injecting highly reactive, in particular H2-rich, fuel in the region of the constriction comprise nozzles which take over a fuel feed.
  • premix burner As far as the design of the premix burner is concerned, it is readily possible to provide it without a transition section between the swirl generator and the mixing tube. Such a premix burner goes out EP-A1-0 321 809 out.
  • a further embodiment of the premix burner provides, in a transition region between the swirl generator and the mixing tube, transition channels for transferring a swirl flow formed in the swirl generator into the flow cross section of the mixing tube arranged downstream of these transition channels.
  • Such a design goes out EP-0 704 657 A1 out.
  • a further embodiment of the premix burner provides to provide a cylindrical or quasi-cylindrical tube, which consists of partial shells, and in which the combustion air flow flows through tangentially arranged air inlet slots or channels in the interior.
  • the desired swirling of the combustion air stream to maximize the desired premix with at least one fuel injected at a suitable point is achieved by a conical or quasi-conically extending in the flow direction of the inner body. mitbewerkstelligt. Such a configuration is for example EP-0 777 081 A1 out.
  • the inventive method is advantageously used to operate a gas turbine plant with at least one combustion chamber.
  • this configuration allows a safe (i.e., greatly reduced flashback probability) lean premix combustion of highly reactive fuels.
  • the injection of the high-reactive fuel takes place via fuel feeds 19 and nozzles 22 directly or in the vicinity of the constriction 18 (see the arrows), where the air velocities of the combustion air are greatest.
  • the cylindrical mixing tube portion 17b downstream of the constriction 18 with its significantly reduced diameter is characterized by high air velocities, which prevent flashback.
  • This section also represents at the same time the mixing section, which allows a good air / fuel mixture at the outlet of the burner assembly 17.
  • An additional important feature of this burner assembly 17 is the utilization of the Venturi effect.
  • the lower static pressure at the throat 18, i. at the point where the fuel is injected means that it is possible to achieve sufficient fuel injection and penetration with relatively low fuel pressures, thereby substantially reducing the use of costly fuel compression.
  • the premix burner is still suitable for lean standard premix operation with natural gas and oil, provided that care is taken that the fuel does not accumulate on the walls of the converging first mixing pipe portion 17a.
  • the burner assembly 16 according to Fig. 2 enables operation with 3 fuels ("tri-fuel operation").
  • Benefits also arise when an improvement of the radial distribution of the fuel due to the divergent streamlines is sought.
  • the method for operating a premix burner according to the invention is particularly suitable for hot gas generation in gas turbine plants, in which fuels are burned with a high H2 content.

Landscapes

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

Claims (11)

  1. Procédé de fonctionnement d'un brûleur à pré-mélange avec un ou plusieurs combustible(s), dans lequel le brûleur à pré-mélange se compose essentiellement d'un générateur de tourbillons ou est équipé en tête d'un générateur de tourbillons, dans lequel le brûleur à pré-mélange présente des moyens pour l'alimentation d'un combustible ainsi que des moyens pour l'introduction d'un courant d'air de combustion, dans lequel un tube de mélange agit en aval du brûleur à pré-mélange ou du générateur de tourbillons et débouche dans une chambre de combustion et présente un étranglement en section transversale (18) en aval du générateur de tourbillons (11a) appartenant au brûleur à pré-mélange (11), et dans lequel l'embouchure du tube de mélange dans la chambre de combustion (14) est formée par un saut de section transversale, qui forme le front de combustion de la chambre de combustion avec une zone de reflux, caractérisé en ce que des moyens (19, 22) pour l'injection d'un combustible hautement réactif (19) sont disposés dans la région de cet étranglement (18), par lesquels on injecte un combustible riche en H2.
  2. Procédé selon la revendication 1, caractérisé en ce que la section transversale du tube de mélange (17, 21) se rétrécit en forme de cône depuis la sortie du brûleur à pré-mélange (11) jusqu'à l'étranglement (18) dans une première partie (17a, 21a) du tube de mélange.
  3. Procédé selon la revendication 2, caractérisé en ce que le tube de mélange (17, 21) est nettement plus petit en section transversale dans une deuxième partie (17b, 21b) du tube de mélange depuis l'étranglement (18) jusqu'à la chambre de combustion (14) que la section transversale à la sortie du brûleur à pré-mélange (11) dans la première partie (17a, 21a) du tube de mélange.
  4. Procédé selon la revendication 3, caractérisé en ce que la deuxième partie (17b) du tube de mélange présente une section transversale constante.
  5. Procédé selon la revendication 3, caractérisé en ce que la section transversale de la deuxième partie (21b) du tube de mélange s'évase légèrement en forme de cône jusqu'à la chambre de combustion (14).
  6. Procédé selon l'une quelconque des revendications 1 à 5, caractérisé en ce que l'injection du combustible hautement réactif est effectuée dans la région de l'étranglement (18) par des buses (22) disposées à cet endroit, et en ce que les buses comprennent une arrivée de combustible correspondante (19).
  7. Procédé selon l'une quelconque des revendications 1 à 6, caractérisé en ce que l'on introduit un combustible liquide par une buse à combustible centrale (5) et/ou un combustible gazeux (13) aux fentes d'entrée d'air tangentielles du générateur de tourbillons respectif.
  8. Procédé selon l'une quelconque des revendications 1 à 7, caractérisé en ce qu'il est prévu dans une région de transition entre le générateur de tourbillons (11a) et le tube de mélange (13, 17, 21) des canaux de transition, au moyen desquels un écoulement d'air de combustion formé dans le générateur de tourbillons est transmis dans la section transversale de passage du tube de mélange (13, 17, 21) disposée en aval des canaux de transition.
  9. Procédé selon l'une quelconque des revendications 1 à 8 pour l'utilisation dans une installation de turbine à gaz pouvant fonctionner avec au moins une chambre de combustion.
  10. Procédé selon l'une quelconque des revendications 1 à 8 pour l'utilisation dans une installation de turbine à gaz avec mise à feu séquentielle.
  11. Procédé selon l'une quelconque des revendications 1 à 8 pour l'utilisation dans une installation combinée.
EP09717497.3A 2008-03-07 2009-02-12 Procédé de fonctionnement d'un brûleur à prémélange Not-in-force EP2260238B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3482008 2008-03-07
PCT/EP2009/051632 WO2009109448A1 (fr) 2008-03-07 2009-02-12 Ensemble brûleur et son utilisation

Publications (2)

Publication Number Publication Date
EP2260238A1 EP2260238A1 (fr) 2010-12-15
EP2260238B1 true EP2260238B1 (fr) 2015-12-23

Family

ID=39523270

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09717497.3A Not-in-force EP2260238B1 (fr) 2008-03-07 2009-02-12 Procédé de fonctionnement d'un brûleur à prémélange

Country Status (4)

Country Link
US (1) US20110056205A1 (fr)
EP (1) EP2260238B1 (fr)
JP (1) JP5449205B2 (fr)
WO (1) WO2009109448A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2299178B1 (fr) * 2009-09-17 2015-11-04 Alstom Technology Ltd Procédé et système de combustion de turbine à gaz pour mélanger sans danger des carburants riches en H2 avec de l'air
GB0920094D0 (en) * 2009-11-17 2009-12-30 Alstom Technology Ltd Reheat combustor for a gas turbine engine
EP2703721B1 (fr) * 2012-08-31 2019-05-22 Ansaldo Energia IP UK Limited Brûleur à prémélange
EP3011231B1 (fr) 2013-06-18 2019-10-30 Woodward, Inc. Ensemble de chambre de combustion de turbine à gaz
US9482433B2 (en) 2013-11-11 2016-11-01 Woodward, Inc. Multi-swirler fuel/air mixer with centralized fuel injection
US9587833B2 (en) 2014-01-29 2017-03-07 Woodward, Inc. Combustor with staged, axially offset combustion
EP2930430A1 (fr) * 2014-04-07 2015-10-14 Siemens Aktiengesellschaft Bec de brûleur et brûleur d'une turbine à gaz
US11940151B2 (en) 2022-01-12 2024-03-26 General Electric Company Combustor with baffle

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4420929A (en) * 1979-01-12 1983-12-20 General Electric Company Dual stage-dual mode low emission gas turbine combustion system
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE4316474A1 (de) * 1993-05-17 1994-11-24 Abb Management Ag Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
DE4409567A1 (de) * 1994-03-21 1995-09-28 Abb Management Ag Verfahren zur Kühlung von thermisch belasteten Komponenten einer Gasturbogruppe
DE4417538A1 (de) * 1994-05-19 1995-11-23 Abb Management Ag Brennkammer mit Selbstzündung
DE4426351B4 (de) * 1994-07-25 2006-04-06 Alstom Brennkammer für eine Gasturbine
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
DE19545026A1 (de) * 1995-12-02 1997-06-05 Abb Research Ltd Vormischbrenner
DE19640198A1 (de) * 1996-09-30 1998-04-02 Abb Research Ltd Vormischbrenner
DE59709446D1 (de) * 1997-10-31 2003-04-10 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
DE19757189B4 (de) * 1997-12-22 2008-05-08 Alstom Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
DE10056243A1 (de) * 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
JP4913746B2 (ja) * 2004-11-30 2012-04-11 アルストム テクノロジー リミテッド 予混合バーナー内の水素を燃焼する方法及び装置
EP1828684A1 (fr) * 2004-12-23 2007-09-05 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange

Also Published As

Publication number Publication date
US20110056205A1 (en) 2011-03-10
EP2260238A1 (fr) 2010-12-15
WO2009109448A1 (fr) 2009-09-11
JP5449205B2 (ja) 2014-03-19
JP2011515641A (ja) 2011-05-19

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