EP2288852B1 - Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre - Google Patents

Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre Download PDF

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Publication number
EP2288852B1
EP2288852B1 EP08873895.0A EP08873895A EP2288852B1 EP 2288852 B1 EP2288852 B1 EP 2288852B1 EP 08873895 A EP08873895 A EP 08873895A EP 2288852 B1 EP2288852 B1 EP 2288852B1
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EP
European Patent Office
Prior art keywords
diffusion
burner
nozzles
fuel
premix
Prior art date
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Application number
EP08873895.0A
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German (de)
English (en)
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EP2288852A1 (fr
Inventor
Eric Norster
Holger Huitenga
Reiner Brinkmann
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.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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Publication of EP2288852A1 publication Critical patent/EP2288852A1/fr
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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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • 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
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • 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
    • F23D2900/14003—Special features of gas burners with more than one nozzle

Definitions

  • the invention relates to a method for operating a premix burner according to claim 1 and a premix burner for carrying out such a method according to claim 5.
  • the pilot flame In addition to stabilizing the combustion process, the pilot flame often also serves to ignite the respective combustion process, so that it is consequently positioned in the vicinity of an ignition orifice of the premix burner. Pollutant emissions are in the background compared to the stabilization of the combustion process.
  • a premix burner for gaseous fuels and a method for controlling this premix burner is in the DE 10 2005 054 442 A1 shown.
  • This premix burner has a multi-stage main injection with a plurality of main nozzles for injecting a gas-air mixture into a flame chamber and a central pilot gas system.
  • a pilot flame of unmixed main fuel is formed via the pilot gas system. From start up to a predetermined load ratio only a certain number of main nozzles are turned on. If a predetermined load ratio is under or exceeded If more main nozzles are switched on or already operated main nozzles are closed.
  • This premix burner for gaseous fuels has a main injection and a central multi-stage pilot gas system.
  • the main injection has a nozzle group of main nozzles for injecting a premixed main fuel.
  • the central multi-stage pilot gas system has a nozzle group of diffusion nozzles for injecting unmixed diffusion fuel and an independently controllable nozzle group of premix nozzles for additional injection of the premixed main fuel.
  • the premix burner When the premix burner is ignited, the largest fuel fraction is introduced via the diffusion stages of the pilot gas system. As the load increases, the premix nozzles of the pilot gas system and main nozzles of the main injection are switched on. The diffusion nozzles are moved back. At full load, the premix nozzles and main nozzles are fully operational and the diffuser nozzles are reduced to a minimum of the total fuel mass flow.
  • a disadvantage of this method is that the stability range of the combustion process, despite the multi-stage pilot gas system is not significantly disseminated. Furthermore, a complex control of the fuel supply is necessary. Furthermore, the premix burner is sensitive to changing fuel compositions.
  • a premix burner and a method having the features of the preamble of claims 1 and 4, respectively, is disclosed in U.S.P. WO 01/59369 A1 disclosed.
  • the object of the present invention is to provide a method for operating a premix burner for gaseous fuels, which is more stable to changing environmental conditions and can be easily adapted to changing fuel compositions and fuel qualities, and a premix burner for carrying out such a method.
  • a method according to the invention provides, via a main injection, a gas-air mixture as main fuel via a.
  • Spin swirl generator into a flame chamber.
  • a diffusion fuel of a central pilot gas system is injected into the flame chamber in the form of at least two partial streams with different directions or orientations.
  • the injection of the diffusion fuel according to the invention as at least two partial streams with different orientations effects a similar effect as a premix.
  • a combustion process with the injection according to the invention shows a substantially improved stability as well as an increased flexibility compared to varying fuel compositions and fuel qualities.
  • the first partial flow is injected transversely or perpendicularly to the flow direction of a main fuel flow that forms in the flame chamber.
  • the second partial flow is injected obliquely to the burner longitudinal axis.
  • the first partial flow transverse to the flow direction of the Hauptbrennstoffstromss causes a similar effect as a premix.
  • the second flow obliquely to the burner longitudinal axis shows less turbulence and a lower mixing than the first partial flow transversely to the flow direction, whereby the diffusion fuel fraction in the flow direction is less sensitive to changes and the respective combustion process is more stable.
  • the gas-air mixture of the main injection is introduced radially into the flame chamber.
  • the gas-air ratio of the main fuel is controlled via the air supply and not via the main fuel nozzles.
  • An inventive premix burner for gaseous fuels has a flame chamber, a Hauptsindüsung for injecting a gas-air mixture as Main fuel in the flame chamber, a swirl generator for swirling the main fuel and arranged in the burner bottom central pilot gas system for injecting a diffusion fuel.
  • the pilot gas system has a multi-stage design with at least one axial diffusion nozzle for injecting a first partial flow of the diffusion fuel and one or more diffusion nozzles arranged obliquely to the longitudinal axis of the burner for feeding in a second partial flow of the diffusion fuel.
  • the at least one employed diffusion nozzle is set in the direction of flow of the main fuel stream.
  • a plurality of axial and annealed diffusion nozzles are provided.
  • the axial diffusion nozzles are located radially on the outside and the employed diffusion nozzles are positioned radially in the interior of the burner bottom.
  • the axial and annealed diffusion nozzles may form two or more concentric circles, the common center being on the burner longitudinal axis.
  • the diffusion nozzles can have different geometries.
  • the diffusion nozzles are formed as bores, grooves or longitudinal slots.
  • the pilot gas system preferably has more axial diffusion nozzles than employed diffusion nozzles. In particular, twice as many axial diffusion nozzles as employed diffusion nozzles can be provided.
  • the premix burner is formed as a can burner with an at least partially cylindrical flame tube which is spaced from the burner bottom via the swirl generator.
  • FIG. 1 shows a highly simplified partial longitudinal section through a premix burner 2 according to the invention for a gas turbine.
  • the premix burner 2 is designed as a can burner with a cylindrical flame chamber 4 for gaseous or liquid fuel. It has a main injection 6 and a central multi-stage pilot gas system 8 according to the invention.
  • the flame chamber 4 is bounded on one side in the axial direction by a burner base 10 and radially by a flame tube 12. A remote from the burner base 10 end portion 14 of the flame tube 12 is widened in a funnel shape.
  • the main injection 6 is used to inject a gas-air mixture as a premixed main fuel 16.
  • the injection takes place radially to the burner longitudinal axis 18 via unspecified main nozzles, which open into a radial swirl generator 20.
  • the main injection has 24 main nozzles.
  • the radial swirl generator 20 is arranged between the burner base 10 and the flame tube 12. It causes the main fuel 16 to be acted upon by a swirl pulse and swirled into the flame chamber 4 occurs. In the flame chamber 4, a main fuel flow whose direction is indicated by the respective arrows.
  • the pilot gas system 8 is used for injecting a non-premixed diffusion fuel and has a multiplicity of axial diffusion nozzles 22a, 22b and a multiplicity of diffusion nozzles 24a, 24b set obliquely to the burner longitudinal axis 18.
  • the diffusion fuel is injected into the flame chamber 4 via the axial diffusion nozzles 22a, 22b and the employed diffusion nozzles 24a, 24b as two partial streams 26, 28.
  • the axial and employed diffusion nozzles 22a, 22b, 24a, 24b are arranged in the burner bottom 10, so that an injection of the partial streams 26, 28 takes place downstream of the entry of the main fuel stream 16.
  • the axial diffusion nozzles 22a, 22b transverse or perpendicular to the flow direction of the main fuel 16 in the flame chamber 4 cause the first partial flow 26 to be intensively mixed with the main fuel 16.
  • the employed diffusion nozzles 24a, 24b are oriented such that the second partial stream 28 is injected into the flame chamber 4 in the flow direction of the main turbulence fuel 16 and the mixing is thus minimized, which promotes the stability of the combustion process.
  • the axial diffusion nozzles 22a, 22b,... and the employed diffusion nozzles 24a, 24b,... form two concentric circles whose common center 30 lies on the burner longitudinal axis 18.
  • the axial diffusion nozzles 22a, 22b,... Are located radially outward and the employed diffusion nozzles 24a, 24b,... Are positioned radially inward.
  • the diffusion nozzles 22a, 22b,..., 24a, 24b,... are uniformly distributed over the respective circle, wherein in the illustrated embodiment, 24 axial diffusion nozzles 22a, 22b,..., And 12 employed diffusion nozzles 24a, 24b,. are provided.
  • the axial diffusion nozzles 22 and the employed diffusion nozzles 24 are formed in this embodiment as bores.
  • a swirled gas-air mixture of the main injection 6 is injected radially into the flame chamber 4 via the radial swirl generator 20.
  • a diffusion fuel as a first partial flow 26 and a second partial flow 28 is injected into the flame chamber 4.
  • the first partial stream 26 is injected via the axial diffusion nozzles 22a, 22b,...
  • the second partial stream 28 into the flame chamber 4 via the employed diffusion nozzles 24a, 24b,.
  • An adjustment of the gas-air ratio of the main fuel 16 to the respective load state via a change in the air supply of the main fuel 16.
  • An adaptation of the gas-air mixture on a known up or Zu Kunststoffung the main nozzles is not provided.
  • the geometry of the diffusion nozzles 22a, 22b,..., 24a, 24b,... is not limited to bores, but that grooves or longitudinal slots are also conceivable.
  • the geometry of the axial or employed diffusion nozzles can vary with each other.
  • the arrangement of the diffusion nozzles 22a, 22b, ..., 24a, 24b, ... is not limited to a circular arrangement, but other arrangements such as star positioning are also conceivable. An uneven distribution of the diffusion nozzles is also possible.
  • a method of operating a premix burner for gaseous fuels with a multi-stage pilot gas system the diffusion fuel is injected as at least two partial streams with different orientations in a flame chamber of the premix burner, and a premix burner for performing the method.

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

Claims (11)

  1. Procédé de fonctionnement d'un brûleur de prémélange (2) pour turbines à gaz comportant les étapes de :
    • injection d'un mélange air-gaz comme combustible principal (16) par l'intermédiaire d'un générateur de tourbillon (20) dans une chambre de flammes (4) disposée longitudinalement à un axe longitudinal de brûleur (18),
    • injection centrale d'un premier flux partiel (26) d'un combustible de diffusion dans la chambre de flammes (4) délimitée vers le haut par une base de brûleur (10) et
    • injection centrale d'un deuxième flux partiel (28) du combustible de diffusion dans la chambre de flammes (4) délimitée vers le haut par la base de brûleur (10),
    caractérisé en ce que
    l'injection du premier flux partiel (26) a lieu par l'intermédiaire d'une buse de diffusion (22a, 22b, ...) axiale et disposée dans la base de brûleur (10) transversalement au flux de combustible principal formé dans la chambre de flammes (4) et
    l'injection du deuxième flux partiel (28) a lieu par l'intermédiaire d'au moins une buse de diffusion (24a, 24b, ...) orientée en biais par rapport à l'axe longitudinal de brûleur (18) et disposée dans la base de brûleur.
  2. Procédé selon la revendication 1, dans lequel le combustible principal (16) est injecté radialement.
  3. Procédé selon la revendication 1 ou 2, dans lequel le rapport air-gaz du combustible principal (16) est réglé par l'intermédiaire de l'alimentation d'air.
  4. Brûleur de prémélange pour turbines à gaz pour mettre en oeuvre le procédé selon la revendication 1 comportant une chambre de flammes (4), une injection principale (6) pour injecter un mélange air-gaz comme combustible principal (16) dans la chambre de flammes (4) par l'intermédiaire d'un générateur de tourbillons (20) pour faire tourbillonner le combustible principal (16) et un système de gaz pilote central (8) réalisé dans la base de brûleur (10) pour injecter un combustible de diffusion, caractérisé en ce que dans la base de brûleur (10) au moins une buse de diffusion axiale (22a, 22b, ...) pour alimenter un premier flux partiel (26) du combustible de diffusion transversalement au flux de combustible principal réalisé dans la chambre de flammes (4) et au moins une buse de diffusion (24a, 24b, ...) orientée en biais par rapport à l'axe longitudinal de brûleur (18) pour injecter un deuxième flux partiel (28) du combustible de diffusion sont disposés.
  5. Brûleur de prémélange selon la revendication 4, dans lequel au moins une buse de diffusion orientée (22a, 22b, ...) est placée dans la direction d'écoulement du flux de combustible principal.
  6. Brûleur de prémélange selon la revendication 5, dans lequel une pluralité de buses de diffusion axiale situées radialement à l'extérieur (22a, 22b, ...) et une pluralité de buses de diffusion orientées radialement situées à l'intérieur (24a, 24b, ...) sont prévues.
  7. Brûleur de prémélange selon la revendication 5 ou 6, dans lequel les buses de diffusion axiale (22a, 22b, ...) et les buses de diffusion orientées (24a, 24b, ...) forment au moins deux cercles concentrique l'un par rapport à l'autre, dont le point central commun (30) est situé sur l'axe longitudinal de brûleur (18).
  8. Brûleur de prémélange selon une des revendications 4 à 7, dans lequel les buses de diffusion axiale (22a, 22b, ...) présentent une autre géométrie que les buses de diffusion orientées (24a, 24b, ...) .
  9. Brûleur de prémélange selon la revendication 8, dans lequel les buses de diffusion axiale (22a, 22b, ...) et les buses de diffusion orientées (24a, 24b, ...) sont des alésages.
  10. Rollers de prémélange selon une des revendications 4 à 9, dans lequel le système de gaz pilote (8) présente plus de plus de buses de diffusion axiale (22a, 22b, ...) que de buses de diffusion orientées (24a, 24b, ...) , notamment le double de buses de diffusion axiale (22a, 22b, ...) que de buses de diffusion orientées (24a, 24b, ...) .
  11. Brûleur de prémélange selon une des revendications 6 à 10, dans lequel la chambre de flammes (4) est délimitée radialement à proximité de la base de brûleur (10) par le générateur de tourbillon (20) et un tube foyer cylindrique (12).
EP08873895.0A 2008-04-16 2008-11-03 Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre Active EP2288852B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008019117A DE102008019117A1 (de) 2008-04-16 2008-04-16 Verfahren zum Betreiben eines Vormischbrenners und ein Vormischbrenner zur Durchführung des Verfahrens
PCT/EP2008/009256 WO2009127240A1 (fr) 2008-04-16 2008-11-03 Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre

Publications (2)

Publication Number Publication Date
EP2288852A1 EP2288852A1 (fr) 2011-03-02
EP2288852B1 true EP2288852B1 (fr) 2016-04-27

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EP08873895.0A Active EP2288852B1 (fr) 2008-04-16 2008-11-03 Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre

Country Status (6)

Country Link
US (1) US10557634B2 (fr)
EP (1) EP2288852B1 (fr)
JP (1) JP5328817B2 (fr)
CA (1) CA2717487C (fr)
DE (1) DE102008019117A1 (fr)
WO (1) WO2009127240A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009054669A1 (de) 2009-12-15 2011-06-16 Man Diesel & Turbo Se Brenner für eine Turbine
EP2400222A1 (fr) * 2010-06-28 2011-12-28 Siemens Aktiengesellschaft Appareil de combustion
EP2629008A1 (fr) 2012-02-15 2013-08-21 Siemens Aktiengesellschaft Injection de carburant inclinée dans une fente de tourbillonnement

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3241162A1 (de) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner
CH672541A5 (fr) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
US5452574A (en) * 1994-01-14 1995-09-26 Solar Turbines Incorporated Gas turbine engine catalytic and primary combustor arrangement having selective air flow control
EP0728989B1 (fr) * 1995-01-13 2001-11-28 European Gas Turbines Limited Appareil de combustion pour moteur de turbine à gaz
GB2333832A (en) * 1998-01-31 1999-08-04 Europ Gas Turbines Ltd Multi-fuel gas turbine engine combustor
FR2788109B1 (fr) * 1998-12-30 2001-06-08 Total Raffinage Distribution Dispositif pour ameliorer le brulage des combustibles gazeux
US6609376B2 (en) 2000-02-14 2003-08-26 Ulstein Turbine As Device in a burner for gas turbines
FR2811410B1 (fr) * 2000-07-10 2002-10-04 Gaz De France Bruleur a melange de gaz et d'air a puissance accrue
JP3590594B2 (ja) * 2001-04-25 2004-11-17 川崎重工業株式会社 ガスタービンエンジン用の液体燃料焚き低ｎｏｘ燃焼器
DE10334228A1 (de) 2002-08-19 2004-03-04 Alstom (Switzerland) Ltd. Verfahren zum Betrieb eines Vormischbrenners sowie Vorrichtung zur Durchführung des Verfahrens
EP1614967B1 (fr) 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
DE102004049491A1 (de) 2004-10-11 2006-04-20 Alstom Technology Ltd Vormischbrenner
JP4015656B2 (ja) * 2004-11-17 2007-11-28 三菱重工業株式会社 ガスタービン燃焼器
US20060191268A1 (en) 2005-02-25 2006-08-31 General Electric Company Method and apparatus for cooling gas turbine fuel nozzles
DE102005015152A1 (de) * 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer
DE502006007811D1 (de) * 2005-06-17 2010-10-21 Alstom Technology Ltd Brenner zur vormischartigen Verbrennung
US20070234735A1 (en) * 2006-03-28 2007-10-11 Mosbacher David M Fuel-flexible combustion sytem and method of operation
EP1890083A1 (fr) * 2006-08-16 2008-02-20 Siemens Aktiengesellschaft Injecteur de carburant pour une turbine à gaz
GB2443431B (en) * 2006-11-02 2008-12-03 Siemens Ag Fuel-injector nozzle

Also Published As

Publication number Publication date
CA2717487C (fr) 2013-01-29
EP2288852A1 (fr) 2011-03-02
US10557634B2 (en) 2020-02-11
DE102008019117A1 (de) 2009-10-22
JP2011513695A (ja) 2011-04-28
WO2009127240A1 (fr) 2009-10-22
US20110167832A1 (en) 2011-07-14
JP5328817B2 (ja) 2013-10-30
CA2717487A1 (fr) 2009-10-23

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