EP0210462B1 - Chambre de combustion double - Google Patents

Chambre de combustion double Download PDF

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Publication number
EP0210462B1
EP0210462B1 EP86109039A EP86109039A EP0210462B1 EP 0210462 B1 EP0210462 B1 EP 0210462B1 EP 86109039 A EP86109039 A EP 86109039A EP 86109039 A EP86109039 A EP 86109039A EP 0210462 B1 EP0210462 B1 EP 0210462B1
Authority
EP
European Patent Office
Prior art keywords
fuel
dual burner
cones
dual
burner according
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
Application number
EP86109039A
Other languages
German (de)
English (en)
Other versions
EP0210462A1 (fr
Inventor
Jean Dr. Hellat
Jakob 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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0210462A1 publication Critical patent/EP0210462A1/fr
Application granted granted Critical
Publication of EP0210462B1 publication Critical patent/EP0210462B1/fr
Expired legal-status Critical Current

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Classifications

    • 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
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising 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
    • F23R3/36—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

Definitions

  • the present invention relates to a dual burner according to the preamble of claim 1. It also relates to a method for mixing air with the liquid fuel flowing into the dual burner.
  • a spiral vortex burner is described in GB-A-817936.
  • a known way of building a detachable swirl body is to provide a tubular jacket with tangential entry slots. This creates a potential vortex that flows axially.
  • vortex breakdown zones in a potential vortex have very poor stability properties.
  • the invention seeks to remedy this.
  • the object of the invention is to produce a stable vortex backflow zone in a dual burner of the type mentioned at the outset.
  • the conditions must be met, according to which the axial profile of the vortex flow generated by the swirl body in the vicinity of the axis has a speed increase, while the swirl must decrease sharply towards the axis.
  • the objectives of the invention are basically achieved in that slotted cones are provided with suitable opening angles; this gives you an optimal opportunity to combine the advantages of a potential vortex tube and a fluid-mechanically perfect swirl body.
  • a vortex flow is obtained which is low in swirl in the center and has an axial speed excess. Because the number of swirls of this burner increases strongly in the axial direction and reaches the breakdown value or the critical value at the end of the burner, this results in a positionally stable vortex backflow zone.
  • Fig. 1 shows a dual burner in the direction of flow to the media used there.
  • the dual burner which is placed in front of the combustion chamber 13 of the combustion chamber, which is only hinted at, is essentially composed of a structure formed into a swirl body, an oil line and a gas line 3.
  • the swirl body structure itself consists of two double-curved plates which are produced by bending flat plates can. The sheets are folded on a certain diagonal and stiffened with a rib (see FIGS. 2, 3, 4). Because the diagonals diverge from each other in the central plane of the flow direction, an arrangement of inner cones is created 4b, 5b, which expand in the flow direction and an arrangement of outer cones 4a, 5a, which taper in the flow direction.
  • the fuels introduced - fuel gas and fuel oil - are introduced individually into the swirl body 1 and thus meet the requirements placed on a dual burner.
  • the oil line 2 divides in front of the swirl body 1 into two oil nozzles 2a, 2b in such a way that their injection is directed axially onto the outer cone 4a, 5a.
  • the pulse of the oil injection at full load is selected so that the oil film 6 penetrates to the end of an outer cone 4a or 5a. With a reduced load, the penetration depth decreases accordingly, so that the outer areas of the vortex flow remain free of fuel. This results in self-regulation, which means that the fuel / air mixture 7a in the vortex center never becomes too lean or too rich.
  • the swirl strength of the vortex flow is dependent on the selected width of the slot that results between the outer cone 4a, 5a and the inner cone 4b, 5b.
  • the outer cones 4a, 5a tapering in the direction of flow thus fulfill various functions. On the one hand, they serve as carriers of the oil film 6 released by the oil nozzles 2a, 2b; Furthermore, the outer cones 4a, 5a serve to guide the flow of the working mixture, which rolls in the axial direction due to the swirl movement.
  • the radiant heat which the sheets receive from the combustion chamber 13 can be partially transferred to the oil film 6 here.
  • the inner cones 4b, 5b which widen in the direction of flow, have fuel lines 8 on the bend end, as a continuation of the gas line 3, which serve to supply a gaseous fuel.
  • the fuel lines 8, which are supplemented with nozzles, also serve to stiffen the swirl body 1. This is closed on the combustion chamber side with a perforated plate 11, through which cooling air or dilution air for the first part of the combustion chamber wall or the combustion chamber 13 can be supplied.
  • the slot widths 14 which are not visible in FIG.
  • the backflow zone 12 begins at the downstream end of the inner cones 4b, 5b.
  • the backflow zone 12 is inherently positionally stable.
  • the taper and expansion rates of the cones 4a, 4b and. 4b, 5b depend on the properties of the combustion chamber, as does the overall length of the swirl body 1.
  • the fuel lines 8 are provided with fuel nozzles 9 which inject the fuel gas towards the center of the swirl body 1.
  • the tangentially flowing air 7 is thus homogeneously enriched with the available fuel gas.
  • the fuel is “rolled in” by the tangentially flowing air 7 between relatively thin layers of air, as a result of which subsequent mixing is unnecessary.
  • the swirl body 1 is closed on the combustion chamber side, as can be seen in FIG. 4, with the perforated plate 11, through which, as already explained, cooling air or dilution air can reach the combustion chamber 13.
  • FIG. 5 shows an expanded variant of the swirl body 1 already shown in FIG. 1.
  • the local version is supplemented with a pilot burner 15.
  • the gas line 3 is extended in the flow direction via the fuel lines 8.
  • the pilot burner version is particularly suitable if the swirl body 1 has more than two pairs of cones.
  • FIGS. 6, 7, 8, 9 - which views can be seen through the planes VI, VII, VIII, IX according to FIG. 5 - the swirl body 1 constructed here from four pairs of cones does not differ conceptually from the one already explained , variant consisting of two pairs of cones.
  • the mixing of the fuels with the tangentially flowing air 7 is easier here, however, because it has to “roll in” smaller fuel rates.
  • the injection of the fuel via the four oil nozzles 2a, 2b, 2c, 2d is also directed axially onto the outer cones 4a, 5a, 16a, 17a.
  • the swirl body 1 now consists of four double-curved sheets 4, 5, 16, 17, which are folded into double cones in the planes of the diagonals 10a, 10b, 10c, 10d. These diagonals run outwards in the direction of flow in a cone-shaped manner, so that the outer cones 4a, 5a, 16a, 17a taper, while the inner cones 4b, 5b, 16b, 17b expand.
  • the inner cones 4b, 5b, 16b, 17b each carry at the end a fuel line 8 provided with fuel nozzles 9, which in cooperation with the rib 10 serves to increase the rigidity of the folded sheets 4, 5, 16, 17.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Claims (6)

1. Brûleur double d'une turbine à gaz ou d'un appareil de production de gaz chauds, se composant essentiellement d'un corps de giration 1 et de moyens d'alimentation de combustibles gazeux et liquides, caractérisé en ce que le corps de giration (1) se compose d'au moins deux tôles (4, 5) doublement incurvées pourvues d'une entrée d'air tangentielle (7), qui sont pliées le long de diagonales (10a, 10b) rayonnant coniquement vers l'extérieur dans le sens de l'écoulement, de telle sorte que l'un des flancs du pli, cintré, forme un cône intérieur (4b, 5b) s'évasant dans le sens de l'écoulement, tandis que l'autre flanc du pli, cintré, forme un cône extérieur (4a, 5a) qui se rétrécit dans le sens de l'écoulement, les flancs de pli cintrés des cônes intérieurs (4b, 5b) s'évasant dans le sens de l'écoulement étant équipés vers leur extrémité d'une conduite de combustible (8) munie d'injecteurs de combustible (9).
2. Brûleur double suivant la revendication 1, caractérisé en ce que les injecteurs de combustible (9) sont orientés vers l'espace intérieur du corps de giration (1).
3. Brûleur double suivant la revendication 1, caractérisé en ce qu'un brûleur pilote (15) est placé en position centrée par rapport aux tôles doublement pliées (4, 5, 16, 17).
4. Brûleur double suivant la revendication 1, caractérisé en ce que l'aire de la section restante en aval entre le contour extérieur du corps de giration (1) et les ouvertures des cônes (4a, 4b ; 5a, 5b ; 16a, 16b ; 17a, 17b) est fermée par une tôle perforée (11).
5. Brûleur double suivant la revendication 1, caractérisé en ce que les diagonales de pliage (10a, 10b, 10c, 10d) sont renforcées par une nervure (10).
6. Procédé pour mélanger de l'air avec le combustible liquide pénétrant dans le brûleur double suivant la revendication 1, caractérisé en ce que l'injection du combustible liquide (2a, 2b, 2c, 2d) est orientée vers les cônes extérieurs (4a, 5a, 16a, 17a), le film (6) qui s'y forme étant de ce fait enroulé par l'air (7) qui pénètre tangentiellement dans les cônes extérieurs (4a, 5a, 16a, 17a).
EP86109039A 1985-07-30 1986-07-02 Chambre de combustion double Expired EP0210462B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3289/85 1985-07-30
CH328985 1985-07-30

Publications (2)

Publication Number Publication Date
EP0210462A1 EP0210462A1 (fr) 1987-02-04
EP0210462B1 true EP0210462B1 (fr) 1989-03-15

Family

ID=4252764

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86109039A Expired EP0210462B1 (fr) 1985-07-30 1986-07-02 Chambre de combustion double

Country Status (6)

Country Link
US (1) US4781030A (fr)
EP (1) EP0210462B1 (fr)
JP (1) JPH06103085B2 (fr)
CA (1) CA1286886C (fr)
DE (1) DE3662462D1 (fr)
IN (1) IN167458B (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108224473A (zh) * 2017-12-28 2018-06-29 中国航发四川燃气涡轮研究院 一种突扩内锥火焰稳定结构的一体化加力燃烧室

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EP1262714A1 (fr) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
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CN100590355C (zh) 2004-02-12 2010-02-17 阿尔斯通技术有限公司 具有限定圆锥形涡旋室的涡旋发生器的、传感器监视的预混合燃烧器
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CN101137868A (zh) 2005-03-09 2008-03-05 阿尔斯通技术有限公司 用于产生可燃燃料/气体混合物的预混燃烧器
CN101137869A (zh) 2005-03-09 2008-03-05 阿尔斯托姆科技有限公司 用于使燃烧室运转的预混燃烧器
EP2116766B1 (fr) * 2008-05-09 2016-01-27 Alstom Technology Ltd Brûleur avec lance à combustible
JP5462527B2 (ja) * 2009-05-19 2014-04-02 大阪瓦斯株式会社 管状火炎バーナ
EP2685161B1 (fr) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Agencement de chambre de combustion, en particulier pour turbine à gaz
EP2685160B1 (fr) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
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Publication number Priority date Publication date Assignee Title
CN108224473A (zh) * 2017-12-28 2018-06-29 中国航发四川燃气涡轮研究院 一种突扩内锥火焰稳定结构的一体化加力燃烧室

Also Published As

Publication number Publication date
JPS6338812A (ja) 1988-02-19
US4781030A (en) 1988-11-01
IN167458B (fr) 1990-10-27
JPH06103085B2 (ja) 1994-12-14
CA1286886C (fr) 1991-07-30
DE3662462D1 (en) 1989-04-20
EP0210462A1 (fr) 1987-02-04

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