EP2252831B1 - Ensemble brûleur et son utilisation - Google Patents

Ensemble brûleur et son utilisation Download PDF

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Publication number
EP2252831B1
EP2252831B1 EP09716501.3A EP09716501A EP2252831B1 EP 2252831 B1 EP2252831 B1 EP 2252831B1 EP 09716501 A EP09716501 A EP 09716501A EP 2252831 B1 EP2252831 B1 EP 2252831B1
Authority
EP
European Patent Office
Prior art keywords
air
burner arrangement
flow
burner
mixing device
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.)
Active
Application number
EP09716501.3A
Other languages
German (de)
English (en)
Other versions
EP2252831A1 (fr
Inventor
Richard Carroni
Marcel Rieker
Adnan Eroglu
Heinz Schaer
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 EP2252831A1 publication Critical patent/EP2252831A1/fr
Application granted granted Critical
Publication of EP2252831B1 publication Critical patent/EP2252831B1/fr
Active 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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/82—Preventing flashback or blowback
    • 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

Definitions

  • the present invention relates to the field of combustion technology. It relates to a burner assembly according to the preamble of claim 1.
  • the according to Fig. 1 apparent premix burner 11 is equipped at the top with a swirl generator and downstream comprises a mixing tube 13, which in turn opens into a combustion chamber 14.
  • This burner assembly 10 extends along an axis 15.
  • the air / fuel mixture 12 generated in the premix burner 11 is injected tangentially between the partial cone shells, which forms a swirl flow, which then in the subsequent mixing tube 13 its complete mixing, learns with the introduced fuel F.
  • the fuel 25 can not only be directed to the swirl generator, but as needed, a subset 25 'of the fuel F is introduced into the mixing tube 13.
  • An additional component of this burner assembly 10 is a arranged in the mixing tube 13 film air ring 16 (in Fig. 1 marked by the dashed box), the task of which is the wall-near flow layers in the mixing tube energetically charged so that the fuel in or stuck to this region can not cause backfire.
  • Essential for the invention is a arranged in the mixing device film air ring for generating or reinforcing a near-wall air film, which is characterized in that it has at least one concentric to the axis annular gap for the injection of air.
  • annular gap Through the use of an annular gap, a broad plane air jet is generated which, compared with the round air jets generated by holes, has a smaller penetration depth into the main flow and more easily conforms to the walls of the mixing tube.
  • An embodiment of the invention is characterized in that a plurality of concentric annular gaps are arranged one behind the other in the direction of the axis. In this way, the flow rate of the injected air can be increased without the penetration depth increases.
  • the annular gaps are equally spaced apart in the axial direction and all have the same gap width (slot width), but this is not necessarily to be understood, because the distance between the slots need not be constant.
  • the slot widths can be made changeable to locally effect a desired film air layer.
  • the influence of the injected air on the boundary layers in the mixing device is further increased by the fact that, according to another embodiment of the invention, the annular gaps are inclined in the flow direction.
  • the film air ring is constructed of a plurality of successively arranged in the axial direction ring elements, which are held to form the annular gaps by means distributed over the circumference arranged supporting elements at a distance.
  • Another embodiment of the invention is characterized in that second means are provided in the annular gap or the annular gaps for producing a tangential component in the air column emerging through the annular gaps in the mixing device, wherein the second means preferably inclined grooves in the walls bounding the annular gaps include.
  • the mixing device is designed as a cylindrical mixing tube and the burner assembly comprises a premix burner, in particular in the form of a double-cone burner, wherein the mixing tube is arranged at the outlet of the premix burner.
  • a further embodiment of a premix burner provides transition channels between the swirl generator and the mixing tube which take over the transfer of a swirl flow forming in the swirl generator into the flow cross section of the mixing tube downstream of these transition channels.
  • 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 burner assembly according to the invention is advantageously used to operate a gas turbine plant with at least one combustion chamber.
  • the burner assembly according to the invention can be used with particular advantage in a gas turbine, which is operated in particular with highly reactive fuels.
  • Fig. 2 shows a preferred embodiment of the newly proposed construction of a film air ring 16 for a burner assembly 10 after Fig. 1 ,
  • the new design is intended to produce a larger and stronger film-air layer near the walls of the mixing tube 13.
  • plane rays have a lower penetration than round rays - in fact, plane rays in a crossing flow tend to adhere more quickly to the walls - those from the WO-A1-2006 / 048405 known rows of holes in the mixing tube 13 according to Fig. 2 replaced by one or more annular gaps 21, which are arranged concentrically or quasi-concentrically to the axis 15.
  • annular gaps 21 air in the form of ring beams (23) is injected into the interior of the mixing tube 13, wherein the air jets 23 create relatively easy to the wall of the mixing tube.
  • the total cross section, the number of gaps 21, the gap width and also the distance between the individual columns can easily be changed in order to change the flow rate of the injected air. Especially easy is the change of the gap width. Furthermore, the gaps 21 can be tilted in the flow direction by a selectable angle in order to further improve the contact of the air jets 23 with the wall of the mixing tube 13.
  • annular air jets 23 a tangential component can be impressed by in the walls of the column 21 corresponding obliquely executed groove 24 (in Fig. 2 if only one groove 24 is shown by way of example).
  • Fig. 2 three columns 21 are consecutively provided at the same distance and with the same gap width.
  • the gaps 21 are formed by four ring-shaped elements 17, 18, 19 and 20 arranged axially one behind the other at a gap width.
  • the adjoining surfaces of the ring elements 17,..., 20 are preferably designed and adapted to one another such that the gaps 21 are uniform Gap width over the entire wall thickness result.
  • the individual ring elements 17, .., 20 are held by local support elements 22 at a distance, which are distributed over the circumference between adjacent ring elements.
  • other manufacturing methods are possible.
  • novel film air ring according to the invention can be used in all fuels. However, it is particularly advantageous for the more reactive fuels (eg, oil or H2-rich fuels) as incinerated in a stationary gas turbine plant.
  • the technique is not limited to AEV burners but can be used successfully in the mixers of other burners.

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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 (16)

  1. Ensemble de brûleur (10), comprenant un dispositif de mélange (13) pour mélanger du combustible et de l'air, de forme tubulaire, s'étendant le long d'un axe (15) dans la direction d'écoulement et débouchant dans une chambre de combustion (14), des premiers moyens (16) pour empêcher un retour d'inflammation du combustible se trouvant dans le dispositif de mélange (13) étant prévus dans le dispositif de mélange (13), lesquels premiers moyens comprennent une bague d'air formant film (16) disposée concentriquement à l'axe (15) pour produire ou renforcer un film d'air proche de la paroi,
    le dispositif de mélange présentant un brûleur à prémélange (11) et un tube mélangeur disposé en aval du brûleur à prémélange, le brûleur à prémélange se composant essentiellement d'un générateur de tourbillon qui se compose d'au moins deux coques coniques partielles creuses emboîtées l'une dans l'autre dans la direction d'écoulement et se complétant pour former un corps,
    la section transversale de l'espace interne formé par les coques coniques partielles creuses augmentant dans la direction d'écoulement,
    les axes de symétrie longitudinaux respectifs de ces coques coniques partielles s'étendant de manière décalée l'un par rapport à l'autre de telle sorte que les parois adjacentes des coques coniques partielles forment, dans leur étendue longitudinale, des fentes d'entrée d'air tangentielles ou des canaux pour l'afflux d'un courant d'air de combustion dans l'espace interne formé par les coques coniques partielles, et
    caractérisé en ce que
    la bague d'air formant film (16) présente au moins une fente annulaire (21) concentrique ou pratiquement concentrique à l'axe (15) en vue de l'injection d'air.
  2. Ensemble de brûleur (10), comprenant un dispositif de mélange (13) s'étendant le long d'un axe (15) dans la direction d'écoulement, de forme tubulaire, débouchant dans une chambre de combustion (14) pour le mélange de combustible et d'air, des premiers moyens (16) pour empêcher un retour d'inflammation du combustible se trouvant dans le dispositif de mélange (13) étant prévus dans le dispositif de mélange (13), lesquels premiers moyens comprennent une bague d'air formant film (16) disposée concentriquement à l'axe (15) pour produire ou renforcer un film d'air proche de la paroi,
    le dispositif de mélange présentant un brûleur à prémélange (11) et un tube mélangeur disposé en aval du brûleur à prémélange, le brûleur à prémélange se composant essentiellement d'un générateur de tourbillon qui se compose d'au moins deux coques coniques partielles creuses emboîtées l'une dans l'autre dans la direction d'écoulement et se complétant pour former un corps,
    la section transversale de l'espace interne formé par les coques partielles creuses s'étendant dans la direction d'écoulement sous forme cylindrique ou pratiquement cylindrique,
    les axes de symétrie longitudinaux respectifs de ces coques partielles s'étendant de manière décalée l'un par rapport à l'autre de telle sorte que les parois adjacentes des coques partielles forment, dans leur étendue longitudinale, des fentes d'entrée d'air tangentielles ou des canaux pour l'afflux d'un air de combustion dans l'espace interne formé par les coques partielles, et de telle sorte que l'espace interne présente un corps interne dont la section transversale diminue dans la direction d'écoulement sous forme conique ou pratiquement conique, et caractérisé en ce que la bague d'air formant film (16) présente au moins une fente annulaire (21) concentrique ou pratiquement concentrique à l'axe (15) en vue de l'injection d'air.
  3. Ensemble de brûleur selon la revendication 1 ou 2,
    caractérisé en ce que dans la direction de l'axe (15), plusieurs fentes annulaires (21) concentriques ou pratiquement concentriques sont disposées les unes derrière les autres.
  4. Ensemble de brûleur selon la revendication 3,
    caractérisé en ce que les fentes annulaires (21) sont espacées de manière équidistante dans la direction axiale.
  5. Ensemble de brûleur selon la revendication 3,
    caractérisé en ce que les fentes annulaires sont espacées dans la direction axiale de manière inégale et/ou variable.
  6. Ensemble de brûleur selon l'une quelconque des revendications 3 à 5,
    caractérisé en ce que les fentes annulaires (21) présentent toutes la même largeur de fente.
  7. Ensemble de brûleur selon l'une quelconque des revendications 3 à 5,
    caractérisé en ce que les fentes annulaires (21) présentent des largeurs de fente différentes.
  8. Ensemble de brûleur selon l'une quelconque des revendications 3 à 7,
    caractérisé en ce que les fentes annulaires (21) sont réalisées sous forme inclinée dans la direction d'écoulement.
  9. Ensemble de brûleur selon l'une quelconque des revendications 1 à 8,
    caractérisé en ce que la bague d'air formant film (16) se compose d'une pluralité d'éléments annulaires (17,.., 20) disposés les uns derrière les autres dans la direction axiale, qui sont maintenus à distance les uns des autres pour former les fentes annulaires (21) au moyen d'éléments de support (22) répartis sur la périphérie.
  10. Ensemble de brûleur selon l'une quelconque des revendications 1 à 9,
    caractérisé en ce que des deuxièmes moyens (24) pour produire une composante tangentielle dans le flux d'air sortant à travers les fentes annulaires (21) dans le dispositif de mélange (13) sont prévus dans la ou les fentes annulaires (21).
  11. Ensemble de brûleur selon la revendication 10,
    caractérisé en ce que les deuxièmes moyens comprennent des rainures s'étendant obliquement (24) dans des parois limitant les fentes annulaires (21).
  12. Ensemble de brûleur selon l'une quelconque des revendications 1 à 11,
    caractérisé en ce qu'un combustible fluide est injecté par le biais d'une buse à combustible centrale (5) dans l'espace interne et/ou un combustible supplémentaire F est injecté par le biais des fentes d'entrée d'air tangentielles du générateur de tourbillon respectif et/ou dans le tube mélangeur.
  13. Ensemble de brûleur selon l'une quelconque des revendications 1 à 12,
    caractérisé en ce que dans une région de transition entre le générateur de tourbillon et le tube mélangeur (13) sont prévus des canaux de transition pour transférer un écoulement d'air de combustion formé dans le générateur de tourbillon, dans la section transversale de passage du tube mélangeur (13) monté en aval des canaux de transition.
  14. Utilisation de l'ensemble de brûleur selon l'une quelconque des revendications 1 à 13 dans une installation de turbine à gaz chauffée au moyen d'au moins une chambre de combustion.
  15. Utilisation de l'ensemble de brûleur selon l'une quelconque des revendications 1 à 14 dans une installation de turbine à gaz chauffée séquentiellement.
  16. Utilisation de l'ensemble de brûleur selon l'une quelconque des revendications 1 à 15 dans une installation combinée.
EP09716501.3A 2008-03-07 2009-02-13 Ensemble brûleur et son utilisation Active EP2252831B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3492008 2008-03-07
PCT/EP2009/051695 WO2009109452A1 (fr) 2008-03-07 2009-02-13 Ensemble brûleur et son utilisation

Publications (2)

Publication Number Publication Date
EP2252831A1 EP2252831A1 (fr) 2010-11-24
EP2252831B1 true EP2252831B1 (fr) 2013-05-08

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Country Status (4)

Country Link
US (1) US8468833B2 (fr)
EP (1) EP2252831B1 (fr)
JP (1) JP5453322B2 (fr)
WO (1) WO2009109452A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2722591A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz
CN111550780A (zh) * 2020-06-09 2020-08-18 广东摩德娜科技股份有限公司 一种气膜保护式预混燃烧器

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Also Published As

Publication number Publication date
US8468833B2 (en) 2013-06-25
JP5453322B2 (ja) 2014-03-26
WO2009109452A1 (fr) 2009-09-11
US20110079014A1 (en) 2011-04-07
EP2252831A1 (fr) 2010-11-24
JP2011515642A (ja) 2011-05-19

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