EP0625673B1 - Brûleur à prémélange pour l'opération d'un moteur à combustion interne, d'une chambre de combustion d'une groupe turbo à gaz ou d'une installation de combustion - Google Patents

Brûleur à prémélange pour l'opération d'un moteur à combustion interne, d'une chambre de combustion d'une groupe turbo à gaz ou d'une installation de combustion Download PDF

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Publication number
EP0625673B1
EP0625673B1 EP94105929A EP94105929A EP0625673B1 EP 0625673 B1 EP0625673 B1 EP 0625673B1 EP 94105929 A EP94105929 A EP 94105929A EP 94105929 A EP94105929 A EP 94105929A EP 0625673 B1 EP0625673 B1 EP 0625673B1
Authority
EP
European Patent Office
Prior art keywords
fuel
throat
premixing burner
operating
fuels
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
EP94105929A
Other languages
German (de)
English (en)
Other versions
EP0625673A2 (fr
EP0625673A3 (fr
Inventor
Klaus Dr. Döbbeling
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.)
ABB AG Germany
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0625673A2 publication Critical patent/EP0625673A2/fr
Publication of EP0625673A3 publication Critical patent/EP0625673A3/fr
Application granted granted Critical
Publication of EP0625673B1 publication Critical patent/EP0625673B1/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
    • 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
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • 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
    • 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
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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 
    • 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
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the invention relates to a premix burner for operation an internal combustion engine, a combustion chamber of a gas turbine group or furnace and an associated process, which are used to burn fuels with very different Properties are suitable.
  • Premix burners ie burners in which the premix zone is an integrated component of the burner itself and which are characterized by low NO x emissions, are known (EP-A1 0 321 809, 0 521 325 and US-A-3 982 392).
  • the invention tries to avoid all these disadvantages. It is based on the task of creating a premix burner for the operation of an internal combustion engine, a combustion chamber of a gas turbine group or a combustion system and an associated method which have low NO x emissions, in which fuels with very different properties can be burned without problems and the function the burner is also ensured outside the design point or in the event of partial failure.
  • this is the case with a premix burner from a swirl generator for the combustion air, a subsequent convergent part, one Narrowing point for the addition of liquid fuel a central lance and a downstream one Diffuser achieved in that the swirl generator is a double-cone burner with adjusted slot width and missing Fuel injection is, and that in the throat supply openings are arranged for further fuels, one Part of these feed openings are aligned radially and for the Supply of gaseous, dusty or liquid fuel is provided and at least a further part of the Feed openings aligned tangentially and for feeding provided by at least one other gaseous fuel is.
  • this is the case with the method for operating the Premix burner achieved in that when operating with gaseous Fuels that have a high flame speed have the fuel through the openings in the constriction opposite to the direction of swirl of the combustion air be injected that when operating with gaseous fuels, which has a low flame speed and a have low calorific value, the fuel through the openings in the constriction in the same direction as the swirl direction of the combustion air be injected, and that when operating with liquid or dusty fuel the fuel in the constriction perpendicular to the direction of flow or just before Constriction with a central lance in the swirled combustion air is injected.
  • the advantages of the invention include that when burning fuels with very different Properties the mixture before reaching the Flame front is complete and the flame does not reach the May interfere with the place of interference.
  • the main reaction zone becomes purely aerodynamic without touching the burner wall, stabilized. There are also no backflow zones, Steps or sudden expansion in the flame zone.
  • the burner also functions outside the design point and secured in the event of partial failure. Furthermore, the burner in an air or fuel graded combustion process applicable.
  • cross-sectional profile is like this is adapted that no flow separation on the wall is possible is.
  • the premix burner, in particular the diffuser is convectively coolable. This is even if the flame is applied to the end area of the diffuser safe burner operation guaranteed.
  • the premix burner shown in Fig. 1 which for combustion of fuels with very different properties is used, consists of a swirl generator 1 for the combustion air 10, a subsequent one convergent part 2, a constriction 3 and a diffuser 4.
  • a flow field with a possible constant total pressure generated Because of the vortex generated you can also the premix burner according to the invention as Designate vortex diffuser burner.
  • the convergent part 2, the constriction 3 and the diffuser 4 are to avoid Secondary flows are rotationally symmetrical and in adapted to their cross-sectional course so that the extension is just so strong that there is no flow separation from the Wall.
  • To the friction losses and, if necessary Keeping the surface to be cooled small is the length of the rotationally symmetrical parts as short as possible. With it result small mixed lengths.
  • the size of the burner can be sufficient under the condition of one high Reynolds number in the burner and under the boundary conditions the desired thermal output and the desired Total length can be chosen arbitrarily.
  • the swirl generator 1 is a double-cone burner with adjusted slot width of the air inlet slots 12 provided without the usual fuel injection.
  • mixing zone i.e. where the fuel-air mixture is present (premix section 6, main reaction zone 7) no internals, e.g. Swirl generator or flame holder, available. Changes in swirl number are dependent on Fuel 9 possible without moving parts in the burner. It are also no backflow zones, steps or sudden extensions the flame zone in place, so that good flame stability (low pulsations) is reached.
  • the main reaction zone 7 is due to the bursting swirl flow (Vortex Breakdown 5) purely aerodynamic, without the Touching the burner wall stabilized.
  • the premix burner is operated with gaseous fuels, which has a high flame speed (short ignition delay times) the fuels must be in opposite directions to the swirl direction of the combustion air 10 in the narrow point 3 be injected (Fig. 2). This will cause the vortex breakdown 5 greatly weakened.
  • gaseous fuels with low flame speed and low calorific value flame stabilization is used by the same direction Injection in relation to the swirl direction of the combustion air and thus by reinforcing the vortex breakdown 5 improved.
  • the burner is a multifunctional system, because of how Fig. 2 shows, for example, low calorie Fuels 9a, natural gas 9b and hydrogen-containing gases 9c be used.

Landscapes

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

Claims (6)

  1. Brûleur à prémélange pour la conduite d'un moteur à combustion interne, d'une chambre de combustion d'un turbogroupe à gaz ou d'une installation de chauffe, se composant d'un générateur de tourbillon (1) pour l'air de combustion (10), d'une partie convergente (2) se raccordant à celui-ci, d'un col (3) pour l'introduction de combustible liquide (9) au moyen d'une lance centrale (11), et d'un diffuseur (4) disposé en aval, caractérisé en ce que le générateur de tourbillon (1) est un brûleur à double cône avec une largeur de fente adaptée et sans injection de combustible, et en ce que des ouvertures (13) pour l'introduction d'autres combustibles (9) sont disposées dans le col (3), une partie de ces ouvertures d'introduction (13) étant orientée radialement et étant prévue pour l'introduction d'un combustible gazeux, pulvérulent ou liquide (9), et au moins une autre partie des ouvertures d'introduction (13) étant orientée tangentiellement et étant prévue pour l'introduction d'au moins un autre combustible gazeux (9).
  2. Brûleur à prémélange suivant la revendication 1, caractérisé en ce que la partie convergente (2), le col (3) et le diffuseur (4) sont réalisés avec une symétrie de révolution.
  3. Brûleur à prémélange suivant la revendication 1 et 2, caractérisé en ce que l'évolution de la section transversale est adaptée de telle façon qu'aucun décollement de l'écoulement à la paroi ne soit possible.
  4. Brûleur à prémélange suivant la revendication 1 et 2, caractérisé en ce que le brûleur à prémélange peut être refroidi entièrement par convection.
  5. Brûleur à prémélange suivant la revendication 1 et 2, caractérisé en ce que le diffuseur (4) peut en priorité être refroidi par convection.
  6. Procédé de conduite d'un brûleur à prémélange suivant la revendication 1, caractérisé en ce que, lors du fonctionnement avec des combustibles gazeux, qui possèdent une vitesse de flamme élevée, les combustibles sont injectés par les ouvertures (13) dans le col (3), à contre-sens par rapport à la direction du tourbillon de l'air de combustion (10), en ce que, lors du fonctionnement avec des combustibles gazeux, qui possèdent une faible vitesse de flamme et un bas pouvoir calorifique, les combustibles sont injectés par les ouvertures (13) dans le col (3), dans le même sens que la direction du tourbillon de l'air de combustion (10), et en ce que, lors du fonctionnement avec un combustible liquide ou pulvérulent, le combustible est injecté dans le col (3) perpendiculairement à la direction d'écoulement ou peu avant le col (3), avec une lance centrale (11), dans l'air de combustion tourbillonnant (10).
EP94105929A 1993-05-17 1994-04-16 Brûleur à prémélange pour l'opération d'un moteur à combustion interne, d'une chambre de combustion d'une groupe turbo à gaz ou d'une installation de combustion Expired - Lifetime EP0625673B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4316474A DE4316474A1 (de) 1993-05-17 1993-05-17 Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
DE4316474 1993-05-17

Publications (3)

Publication Number Publication Date
EP0625673A2 EP0625673A2 (fr) 1994-11-23
EP0625673A3 EP0625673A3 (fr) 1995-05-17
EP0625673B1 true EP0625673B1 (fr) 1999-03-24

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP94105929A Expired - Lifetime EP0625673B1 (fr) 1993-05-17 1994-04-16 Brûleur à prémélange pour l'opération d'un moteur à combustion interne, d'une chambre de combustion d'une groupe turbo à gaz ou d'une installation de combustion

Country Status (4)

Country Link
US (1) US5673551A (fr)
EP (1) EP0625673B1 (fr)
JP (1) JPH06341617A (fr)
DE (2) DE4316474A1 (fr)

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DE102007043626A1 (de) * 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
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EP2107313A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Alimentation étagée de combustible dans un brûleur
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EP2420730B1 (fr) * 2010-08-16 2018-03-07 Ansaldo Energia IP UK Limited Brûleur de post-combustion
TWI435978B (zh) * 2011-10-31 2014-05-01 Atomic Energy Council 富氫氣體燃燒器
EP2703721B1 (fr) * 2012-08-31 2019-05-22 Ansaldo Energia IP UK Limited Brûleur à prémélange
US9194583B2 (en) * 2013-02-20 2015-11-24 Jorge DE LA SOVERA Mixed fuel vacuum burner-reactor
WO2014181951A1 (fr) * 2013-05-07 2014-11-13 한국기계연구원 Chambre de combustion du type à prémélange d'une structure de tube de venturi à des fins de réduction des émissions
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EP4056903A1 (fr) * 2021-03-07 2022-09-14 CPS-Holding Limited Moteur de combustion de turbines à gaz alimenté à l'hydrogène

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Also Published As

Publication number Publication date
EP0625673A2 (fr) 1994-11-23
EP0625673A3 (fr) 1995-05-17
US5673551A (en) 1997-10-07
JPH06341617A (ja) 1994-12-13
DE59407984D1 (de) 1999-04-29
DE4316474A1 (de) 1994-11-24

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