EP0987491B1 - Procédé pour prévenir les instabilités d'écoulement dans un brûleur - Google Patents

Procédé pour prévenir les instabilités d'écoulement dans un brûleur Download PDF

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Publication number
EP0987491B1
EP0987491B1 EP98810924A EP98810924A EP0987491B1 EP 0987491 B1 EP0987491 B1 EP 0987491B1 EP 98810924 A EP98810924 A EP 98810924A EP 98810924 A EP98810924 A EP 98810924A EP 0987491 B1 EP0987491 B1 EP 0987491B1
Authority
EP
European Patent Office
Prior art keywords
air
fuel
combustion
disturbance
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
EP98810924A
Other languages
German (de)
English (en)
Other versions
EP0987491A1 (fr
Inventor
Christian Oliver Dr. Paschereit
Jakob Prof. Dr. Keller
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.)
GE Vernova 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
Priority to EP98810924A priority Critical patent/EP0987491B1/fr
Priority to DE59812944T priority patent/DE59812944D1/de
Priority to US09/382,628 priority patent/US6390805B1/en
Priority to JP11254540A priority patent/JP2000104923A/ja
Publication of EP0987491A1 publication Critical patent/EP0987491A1/fr
Application granted granted Critical
Publication of EP0987491B1 publication Critical patent/EP0987491B1/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
    • 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
    • F23C7/02—Disposition of air supply not passing through burner
    • 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
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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

Definitions

  • the present invention relates to Method for operating a burner, according to the preamble of claim 1.
  • the invention relates also to a burner according to the preamble of claim 2.
  • EP-B1-0 321 809 is a burner for liquid and gaseous fuels known with premix, in which externally supplied combustion air moved tangentially between at least two entry slots arranged, hollow half-cones enters and there in the direction of the combustion chamber flows, and in which on the side facing away from the combustion chamber, the tapered side the half-cones of the liquid fuel is injected centrally.
  • the fuel will so to speak, captured and "enveloped" by the combustion air, so that forms a conical liquid fuel profile between the half-cones, which expands in the direction of the combustion chamber and burns there.
  • gaseous Fuel is taken from fuel supply pipes that run along the air intake slots run, injected through rows of holes across the incoming air.
  • thermoacoustic oscillations are primarily responsible for an important class 1 of reaction rate variations induced thermoacoustic oscillations.
  • These largely coherent waves result in a burner of the above Type under typical operating conditions to vibrations with frequencies of about 100 Hz. Since this frequency has typical fundamental eigenmodes of Of many torches of gas turbines coincide, represent the thermoacoustic Oscillations are a problem.
  • EP-A2-0 851 172 discloses a burner for operating a combustion chamber with a liquid and / or gaseous fuel.
  • a burner for operating a combustion chamber with a liquid and / or gaseous fuel the required combustion air passed through tangential air inlet channels in an interior of the burner.
  • This flow is created in the interior of a swirl flow, which at the output of Burner induces a backflow zone.
  • At least one zone is provided in each part body forming the burner, within which inlet openings for the injection of additional air into the swirl flow are provided.
  • this injection forms on the inner wall of the body part Film, which prevents the flame along the inner wall of the part body in the interior of the burner can strike back.
  • the invention is therefore based on the object a procedure and to provide a burner for carrying out the method, which provides for the formation of coherent flow instabilities of the combustion air flow after exiting into the Combustion chamber prevented.
  • Another embodiment of the invention is characterized in that it the burner is a double - cone burner, that the injection of the Disturbance air through interference nozzles, and that the disturbance air directly at the leading edges of the half-cones takes place where the shear layers form. Furthermore, it is preferred that the disturbance nozzles be uniform in certain Distributes intervals on the sizes of leading edges of half-cones, becomes so the periodicity of the waves on the shear layers disrupted what the prevention the thermoacoustic oscillations targeted causes in the nucleus of their formation.
  • FIG. 1 shows a section through an idealized shear layer 10, as assumed for the subsequent calculations.
  • the shear layer 10 is of a thickness h, and the coordinate system is laid so that the axes x and z are in the shear layer, the axis y is perpendicular thereto, and the main flow direction (longitudinal) is along x.
  • the origin of the coordinate system is such that the thickness of the shear layers 10 extends along y from -h / 2 to + h / 2, and that the layer at the top in the figure moves along x at a velocity U o Moves to the right, while the layer shown in Figure 1 below moves at a speed -U o along x to the left.
  • a is the growth exponent of the perturbation in 1 / s
  • U 0 is the edge velocity at the shear layer 10
  • k z is the Component of the wave vector along z, ie in the transverse direction.
  • FIG. 5 shows various views of a double-cone burner 26, based on which the technical realization of the above-described principle is to be shown.
  • figure 5a shows a perspective view of a double-cone burner 26.
  • the combustion air 14 enters laterally through the entry slots 23 of the slightly shifted Axes arranged, hollow half-cones 18 and 21, flows to the front end the burner 26 with description of a slight arc, and occurs after passing the leading edge 24 of the half-cones 18, 21 from the burner 26 into the combustion chamber 28.
  • Am tapered end of the half-cones 18, 21 is a cylindrical part 20, in which a fuel nozzle 19 is arranged, which in this case liquid Insert fuel centrally between the two half-cones 18 and 21.
  • the combustion air 14 envelops the injected fuel, and it forms a fuel cone, which expands towards the front, and which as a mixture 15 of combustion air 14 and fuel and Greunstaff after exiting into the Combustion chamber 28 burns at the burner mouth 27 in a flame 17.
  • FIG. 5c) shows a view from above onto the double-cone burner 26.
  • the spacing of the stub nozzles 16 can be easily traced.
  • the transversal perturbation must be such that the perturbation nozzles 16 generate perturbation air streams which are 5 cm apart in the x-direction, ie in the flow direction of the mixture.
  • FIG. 5d) shows a schematic front view of a double-cone burner 26. Again, the orthogonal intermingling of the mixture 15 and the interfering air 22 is recognizable.
  • the injected air flow 22 has no strong, inwardly directed components, so that the mixture 15 is not disturbed .
  • the total pressure of the injection of the disturbance air 22 must be at least as great as the total pressure of the mixture flowing past 15, so that significant transversal disturbances can form at all.

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

Claims (5)

  1. Procédé de conduite d'un brûleur à prémélange (26), se composant de demi-cônes creux (18, 21) disposés de façon décalée, dans lequel
    on injecte un courant d'air de combustion (14) tangentiellement par au moins deux fentes d'entrée (23) formées par les demi-cônes,
    on injecte un combustible en position centrale et/ou on injecte un combustible gazeux dans l'écoulement d'air de combustion entrant transversalement,
    le courant d'air de combustion (14) est prémélangé avec du combustible à l'intérieur du brûleur (26), et le mélange combustible/air (15) qui se forme est transporté dans une chambre de combustion (28) faisant suite au brûleur (26),
    dans laquelle le mélange combustible/air (15) est brûlé en formant des gaz chauds,
    dans lequel il se forme dans la chambre de combustion (28) des instabilités d'écoulement cohérentes après la sortie du mélange combustible/air (15) dans la chambre de combustion (28) par suite d'une couche de cisaillement (10) entre le mélange sortant (15) et les gaz chauds, et
    dans lequel on injecte un air de perturbation (22) dans le mélange combustible/air (15),
    caractérisé en ce que l'on injecte l'air de perturbation (22) dans le courant de mélange combustible/air (15), immédiatement aux arêtes avant (24) des demi-cônes, de manière sensiblement perpendiculaire à la direction principale d'écoulement du mélange combustible/air (15) et de manière sensiblement parallèle à la couche de cisaillement (10).
  2. Brûleur à prémélange pour la mise en oeuvre du procédé, dans lequel
    le brûleur à prémélange (26) se compose de demi-cônes creux (18, 21), disposés de façon décalée, qui forment au moins deux fentes d'entrée (23) pour un air de combustion (14),
    les demi-cônes (18, 21) sont limités par des arêtes avant (24) du côté de la chambre de combustion,
    une partie cylindrique (20) avec un injecteur de combustible est disposée à l'extrémité rétrécie des demi-cônes (18,21),
    les demi-cônes (18, 21) présentent des injecteurs de perturbation (16) pour l'injection d'air de perturbation,
    caractérisé en ce que
    les injecteurs de perturbation (16) sont insérés immédiatement avant les arêtes avant (24) des demi-cônes (18, 21), de telle façon qu'ils injectent un air de perturbation (22) perpendiculairement à la direction d'écoulement principale d'un mélange combustible/air (15) sortant dans la chambre de combustion (28) dans la couche de cisaillement (10) qui se forme en aval des arêtes avant (24) et de manière sensiblement parallèle à cette couche de cisaillement.
  3. Brûleur à prémélange selon la revendication 2, caractérisé en ce qu'il est prévu une pluralité d'injecteurs de perturbation (16) et en ce que les injecteurs de perturbation (16) sont répartis uniformément sur les pourtours des demi-cônes (18, 21).
  4. Brûleur à prémélange selon la revendication 3, caractérisé en ce que
    l'espacement uniforme des injecteurs de perturbation (16) est choisi de façon à être égal ou inférieur à une valeur critique, et
    cette valeur critique résulte de la vitesse d'écoulement de l'air de combustion et de la fréquence des instabilités d'écoulement cohérentes du mélange combustible/air (15) se produisant avec le brûleur sans injecteurs de perturbation (16),
    de telle façon que la valeur critique soit donnée par le quotient de la vitesse d'écoulement de l'air de combustion (14) et de la fréquence des instabilités d'écoulement cohérentes se produisant avec le brûleur sans injecteurs de perturbation (16), multiplié par 0,312.
  5. Brûleur à prémélange selon la revendication 4, caractérisé en ce que, avec le brûleur à prémélange (26) sans injecteurs de perturbation, pour une fréquence des instabilités d'écoulement cohérentes du courant d'air de combustion (15) de l'ordre de 100 à 125 Hz et pour une vitesse d'écoulement de l'air de combustion (15) de l'ordre de 20 à 30 m/s, les injecteurs de perturbation (16) présentent sur les demi-cônes (18, 21) un espacement de l'ordre de 3 à 5 cm, en particulier de l'ordre de 4,5 à 5 cm.
EP98810924A 1998-09-16 1998-09-16 Procédé pour prévenir les instabilités d'écoulement dans un brûleur Expired - Lifetime EP0987491B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP98810924A EP0987491B1 (fr) 1998-09-16 1998-09-16 Procédé pour prévenir les instabilités d'écoulement dans un brûleur
DE59812944T DE59812944D1 (de) 1998-09-16 1998-09-16 Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner
US09/382,628 US6390805B1 (en) 1998-09-16 1999-08-25 Method of preventing flow instabilities in a burner
JP11254540A JP2000104923A (ja) 1998-09-16 1999-09-08 バ―ナにおける流動不安定性を回避するための方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810924A EP0987491B1 (fr) 1998-09-16 1998-09-16 Procédé pour prévenir les instabilités d'écoulement dans un brûleur

Publications (2)

Publication Number Publication Date
EP0987491A1 EP0987491A1 (fr) 2000-03-22
EP0987491B1 true EP0987491B1 (fr) 2005-07-20

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EP98810924A Expired - Lifetime EP0987491B1 (fr) 1998-09-16 1998-09-16 Procédé pour prévenir les instabilités d'écoulement dans un brûleur

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US (1) US6390805B1 (fr)
EP (1) EP0987491B1 (fr)
JP (1) JP2000104923A (fr)
DE (1) DE59812944D1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10000415A1 (de) 2000-01-07 2001-09-06 Alstom Power Schweiz Ag Baden Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
DE50212753D1 (de) 2001-07-26 2008-10-23 Alstom Technology Ltd Vormischbrenner mit hoher Flammenstabilität
US10240784B2 (en) * 2013-06-17 2019-03-26 Schlumberger Technology Corporation Burner assembly for flaring low calorific gases
CN115751378B (zh) * 2022-11-10 2024-10-18 南昌航空大学 一种带梯形筋条和三角凸块的支板火焰稳定器

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0851172A2 (fr) * 1996-12-23 1998-07-01 Abb Research Ltd. Brûleur pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide ou gazeux

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
GB1134996A (en) 1967-04-21 1968-11-27 Lev Iosifovich Sorkin Jet noise suppressor in jet engine
US3788065A (en) * 1970-10-26 1974-01-29 United Aircraft Corp Annular combustion chamber for dissimilar fluids in swirling flow relationship
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
JPS5632961A (en) 1979-08-25 1981-04-02 Minamoto:Kk Oshizushi (pressed vinegared fish and rice) of yellowtail and its preparation
JPS5632962A (en) 1979-08-27 1981-04-02 Hiroji Shimizu Forming device for maki (rolled)sushi (vinegared rice with fish and vegetables)
JPS57108507A (en) * 1980-12-25 1982-07-06 Matsushita Electric Ind Co Ltd Gun type burner
JPS57108508A (en) * 1980-12-25 1982-07-06 Matsushita Electric Ind Co Ltd Gun type burner
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH680467A5 (fr) * 1989-12-22 1992-08-31 Asea Brown Boveri
US5345768A (en) * 1993-04-07 1994-09-13 General Electric Company Dual-fuel pre-mixing burner assembly
ATE170968T1 (de) * 1995-07-20 1998-09-15 Dvgw Ev Verfahren und vorrichtung zur unterdrückung von flammen-/druckschwingungen bei einer feuerung

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0851172A2 (fr) * 1996-12-23 1998-07-01 Abb Research Ltd. Brûleur pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide ou gazeux

Also Published As

Publication number Publication date
US6390805B1 (en) 2002-05-21
DE59812944D1 (de) 2005-08-25
JP2000104923A (ja) 2000-04-11
EP0987491A1 (fr) 2000-03-22

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