EP1141628B1 - Bruleur pour generateur de chaleur - Google Patents

Bruleur pour generateur de chaleur Download PDF

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Publication number
EP1141628B1
EP1141628B1 EP99959164A EP99959164A EP1141628B1 EP 1141628 B1 EP1141628 B1 EP 1141628B1 EP 99959164 A EP99959164 A EP 99959164A EP 99959164 A EP99959164 A EP 99959164A EP 1141628 B1 EP1141628 B1 EP 1141628B1
Authority
EP
European Patent Office
Prior art keywords
swirl generator
swirl
flow
burner
fuel
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
EP99959164A
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German (de)
English (en)
Other versions
EP1141628A1 (fr
Inventor
Klaus 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.)
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 EP1141628A1 publication Critical patent/EP1141628A1/fr
Application granted granted Critical
Publication of EP1141628B1 publication Critical patent/EP1141628B1/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
    • 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
    • F23D14/62—Mixing devices; Mixing tubes
    • 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
    • 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
    • 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
    • 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
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • 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
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • 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
    • F23D2900/11002—Liquid fuel burners with more than one nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07002—Injecting inert gas, other than steam or evaporated water, into the combustion chambers

Definitions

  • the present invention relates to a burner for operating a heat generator according to the preamble of the independent claim.
  • a burner is from EP 0 797 051 A2.
  • a first high pressure combustor preferably with premix burners (see EP-0 321 809 B1) equipped, produces a hot gas, which after a partial relaxation in a first high-pressure turbine in a second Brennsch (reheat combustion chamber) flows, in which the partially relaxed Hot gas is reheated to the maximum turbine inlet temperature, with which such a gas turbine based on a sequential combustion.
  • a such gas turbine is from US-5,454,220, US-5,577,378 and EP-0 620 362 A1 forth.
  • the so-called reheat combustion chamber has a configuration which in the publications EP-0 745 809 A1 and EP-0 835 996 A1 shown in more detail and is described.
  • the invention aims to remedy this situation.
  • the invention as claimed in claim 1 is characterized, is the object of a Premix burner of the type mentioned above listed above Fix imperfections.
  • the mixture of combustion air i. the partially relaxed Hot gases and fuel
  • a round mixing section which mixing section is filled by a single swirl flow.
  • For swirl generation are in the still rectangular held inlet cross-section a conical consisting of several partial bodies swirl generator or swirl generator blades installed, which a twisting of the combustion air form.
  • the formed by the swirler blades or between The individual sub-bodies of the swirl generator existing entry slots are preferably of constant slot width, but they can be along their barrel length have a variable slot width.
  • Such swirl generation largely corresponds to one those according to DE 44 35 266 A1.
  • a difference to this swirl generation is that the inventive swirl generator in a first rectangular inflow channel is integrated, this over the run length of the swirl generator in a channel with approximately square or round Cross-section is transferred, with a clean flow to the swirler inlet slots is respected, this at best flow separation too avoid.
  • a fuel distribution system for gaseous and / or liquid fuels Integrated into the swirl generator is a fuel distribution system for gaseous and / or liquid fuels, the fuel distribution thereby along the Entry slots, as is apparent from the latter document, or through the trailing edges of the swirl blades or through axial injection the fuel from the blade surface out, here it primarily for the injection of a low or medium calorific fuel (LBTU, MBTU) goes.
  • LBTU low or medium calorific fuel
  • MBTU medium calorific fuel
  • Liquid fuels are beneficial at injected upstream of the swirl generator by a plurality of individual jets, where it has been shown that it is extremely advantageous if the Number of individual beams with the number of inlet slots in the swirl generator or the number of Draliermaschineerschaufeln matches.
  • the supply of liquid fuel must therefore preferably outside the axis done by the above-mentioned multiple nozzle system.
  • the flow is in a cylindrical mixing tube guided.
  • the transition from the swirl generator to the mixing tube is to be designed in such a way that that the flow cross-sectional area is almost constant and no separations occur. This can be done either by a specially shaped transition piece or by immersing the swirler blades in the cylindrical Channel happen. Another possibility is the swirler blades with a cutaway trailing edge in the axial direction too Mistake.
  • the length of the mixing tube is chosen so that of the Fuel injection until the end of the mixing tube, the autoignition of the selected fuels is not exceeded. Depending on the size of the Burner and depending on the selected burner pressure loss, the Length of the mixing section between zero and two burner diameters vary.
  • a differently shaped Demolition edge can be attached, which is due to the Coanda effect a convexly curved end portion stabilizes the boundary layer and the entire Flow deflects outwards. This will on the one hand achieved that the Flow in the combustion chamber moves faster to the wall and faster is delayed, so that can set a turbulent flame front. On the other hand, the delay at the end of the mixing tube part of the recovered dynamic pressure in the sense of a diffuser effect.
  • the swirl intensity can be adjusted so much that downstream of the mixing section a remindström which arises on the axis, preferably the swirl strength but be so great that the flow downstream of the mixing tube within a Mixing tube diameter on the axis only at speeds smaller the cross-sectional average combustion chamber velocity is delayed.
  • the turbulent ones generated at this lossy delay Velocity fluctuations are used for flame stabilization.
  • the fuel supply to the swirl generator is done by one to the burner axis radially extending fuel and cooling air supply.
  • the swirl generators can be attached to the fuel supply and with this radially from the gas turbine be removable without the housing must be lifted.
  • Fig. 1 shows the overall structure of a burner system for operating a combustion chamber.
  • the burner system basically consists of four operating stages, which each fulfill a certain function and among themselves in an interdependent Process flow.
  • the first section consists of one hand an inflow passage 10 for a combustion air flow, in which inflow passage 10 a swirl generator 100 is arranged.
  • the in this swirl generator 100 swirl flow formed is arranged on the basis of a downstream Transition geometry 200 transferred without separation into a mixing tube 20.
  • a such transition geometry 200 is in the document DE 44 35 266 A1 under Fig. 6 is shown and described.
  • Abströmungs furnish of the mixing tube 20 is located the actual combustion chamber 30, which here only by the flame tube is a picture-picture light.
  • the mixing tube 20 satisfies the condition that downstream of Swirl generators 100 a defined mixing distance is provided, in which a perfect premix of fuels of various types is achieved.
  • This mixing section, so the mixing tube 20, further allows a lossless flow guidance, so that also in operative connection with the Transition geometry 200 initially can not form a backflow zone, which along the length of the mixing tube 20 on the quality of mixing for all types of fuel Influence can be exercised.
  • This mixing tube 20 has one more another characteristic being that in the mixing tube itself the axial velocity profile has a pronounced maximum on the axis, so that a flashback of the flame from the combustion chamber 30 is not possible. However, it is true that with such a configuration, this axial velocity falls off towards the wall.
  • the mixing tube 20 in the flow and circumferential direction with a number of regularly or irregularly distributed holes 21 most different Cross sections and directions provided by which a Air quantity flows into the interior of the mixing tube 20, and along the wall in the Meaning of a filming an increase in prevailing speed induced.
  • Another way to achieve the same effect is that the flow cross-section of the mixing tube 20 downstream the transition geometry 200 undergoes a constriction, whereby the entire speed level within the mixing tube 20 is raised becomes.
  • these holes 21 extend at an acute angle opposite the burner axis 60.
  • the outlet corresponds to the Transition geometry the narrowest flow cross-section of the mixing tube 20th
  • the said transition geometry 200 thus bridges the respective one Cross-sectional difference, without negatively affecting the flow formed influence. If the chosen precaution in guiding the pipe flow 40 along the mixing tube 20 an intolerable pressure drop can be remedied by this at the end of the Mixing tube 20 a in the figure not shown in detail diffuser is provided. At the end of the mixing tube 20 then closes the already mentioned Combustion chamber 30, wherein between the two flow cross-sections a Cross-section jump is present. Only here does a central backflow zone form 50, which has the characteristics of a bodiless flame holder having.
  • Fig. 2 shows the head stage of the burner.
  • the quadrangular inflow channel 10 as well as the swirl generator 100 integrated therein are shown here.
  • This inflow channel 10 forms an autonomous burner unit and in conjunction with a number of further juxtaposed inflow channels an annular Combustion chamber, preferably for the operation of gas turbines, in particular one Nachbrennhunt, as is apparent from EP 0 620 362 A1, Figure Pos.
  • the inflow passage 10 is on the head side of rectangular shape, over the run length of the swirl generator 100 it goes over in a square cross-section.
  • the swirl generator (100) consists of at least two hollow, conical, nested in the flow direction partial bodies 101, whose respective longitudinal axis of symmetry offset each other so run that the adjacent walls of the body part 101 in the Longitudinal tangential channels 102 for the inflow of combustion air 115 in an inner space 103 formed by the partial bodies 101 exhibit. With effect on this interior is at least one fuel nozzle intended.
  • Fig. 3 shows another embodiment of a swirl generator, which without can be further integrated into the inflow duct according to FIG.
  • This Swirl generator 150 consists of a central body 151, which has a radial or quasi-radial conduit 152 for the supply of fuels 153, 154 having.
  • On this central body 151 are individual swirl vanes 156 anchored, which extend in the axial direction. Covered in a jacket these swirl vanes are separated by a tube 155 which is open at each end, on the one hand on the head side for the inflow of the combustion air 115 (see FIG. and on the other drain side for the further flow of the twisted combustion air (see Fig. 1), whereby it is opposite to the swirl generator according to Fig.
  • a decentralized fuel injection 154a of the liquid fuel 154 becomes the injection angle of the fuel jet associated with the fuel nozzle 154a relative to the axis, preferably approximately the angle of attack of Swirl vanes 156 equated.
  • a multi-shell swirl generator of a burner as for example from EP 0 321 809 B1 or from the swirl generators 1 (see the references cited therein), are suitable Good as injection position of the fuel, the trailing zones along the Lee side of the corresponding shell, or the guide vanes or the Swirl vanes of a suitably designed swirl generator. There it is Drop spray exposed to lower aerodynamic forces, and he will accordingly blended better radially into the combustion air.
  • the number of injection points is adapted to the burner design, wherein At least one injection per shell or blade is provided.

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

Abstract

L'invention concerne un brûleur servant au fonctionnement d'un générateur de chaleur. Ledit brûleur est constitué essentiellement d'un générateur de tourbillons (100) pour un flux d'air de combustion (115) et de moyens pour injecter au moins un carburant dans le flux d'air de combustion (115). En aval du générateur de tourbillons (100) est placée une section de mélange (20) qui, dans une première partie, dans le sens du flux, présente un nombre de canaux dans une pièce de transition (200), lesquels servent à transférer un écoulement produit dans le générateur de tourbillons (100) dans un tube de mélange (20) placé en aval de ladite pièce de transition (200). Une chambre de combustion (30) est située en aval du tube de mélange (20). Le générateur de tourbillons (100) est intégré dans une section d'entrée de flux (10) autonome qui est soumise au flux d'air de combustion (115).

Claims (10)

  1. Brûleur pour faire fonctionner un générateur de chaleur, dans lequel le brûleur se compose essentiellement d'un générateur de tourbillon (100, 150) pour un courant d'air de combustion (115) et de moyens pour l'injection d'au moins un combustible dans le courant d'air de combustion (115), en aval du générateur de tourbillon (100, 150) étant disposée une section de mélange qui présente, à l'intérieur d'une première partie de section dans la direction d'écoulement, une pluralité de canaux dans une pièce de transition (200) pour le transfert d'un écoulement formé dans le générateur de tourbillon (100, 150) dans un tube de mélange (20) monté après en aval de cette pièce de transition (200), en aval de ce tube de mélange (20) étant disposée une chambre de combustion (30) formée par un élargissement de section transversale,
    caractérisé en ce que
    le générateur de tourbillon (100, 150) est intégré dans un canal d'afflux (10) dans lequel entre le courant d'air de combustion (115), la section transversale d'écoulement du canal d'afflux (10) passant d'une forme en section transversale rectangulaire du côté de la tête sur toute la longueur du générateur de tourbillon (100, 150) dans une forme en section transversale approximativement carrée ou ronde.
  2. Brûleur selon la revendication 1,
    caractérisé en ce que le générateur de tourbillon (100, 150) se compose d'au moins deux corps partiels (101) creux, de forme conique, emboítés l'un dans l'autre dans la direction de l'écoulement, en ce que les axes de symétrie longitudinaux respectifs de ces corps partiels (101) sont décalés l'un par rapport à l'autre de telle sorte que les parois adjacentes des corps partiels (101) libèrent dans leur étendue longitudinale des canaux tangentiels (102) pour l'entrée du courant d'air de combustion (115) dans une chambre interne (103) formée par les corps partiels (101).
  3. Brûleur selon la revendication 2,
    caractérisé en ce que l'on prévoit au moins une buse d'injection de combustible agissant sur la chambre interne (103).
  4. Brûleur selon la revendication 3,
    caractérisé en ce que
    les corps partiels (101) présentent un profilage en forme d'aube en section transversale.
  5. Brûleur selon la revendication 1,
    caractérisé en ce que
    le générateur de tourbillon (100, 150) se compose d'une pluralité d'aubes tordues (156) qui sont intégrées dans une enveloppe fermée.
  6. Brûleur selon la revendication 5,
    caractérisé en ce que
    le générateur de tourbillon (100, 150) présente des moyens pour l'injection (153a, 154a) d'au moins un combustible (153, 154).
  7. Brûleur selon la revendication 5 ou 6,
    caractérisé en ce que
    le générateur de tourbillon (100, 150) présente au moins une buse d'injection de combustible (154a) du côté de la tête, et en ce que la buse d'injection de combustible (154a) est orientée approximativement en face de l'axe du brûleur (60) en fonction de l'angle d'attaque des aubes tordues (156).
  8. Brûleur selon la revendication 3 ou 7,
    caractérisé en ce que
    le nombre des buses d'injection de combustible (154a) correspond au moins au nombre des éléments formant le tourbillon (101, 156) du générateur de tourbillon (100, 150).
  9. Brûleur selon la revendication 2 ou 5,
    caractérisé en ce que
    le nombre des canaux dans la pièce de transition (200) correspond au nombre des courants partiels entraínés en rotation formés par le générateur de tourbillon (100, 150).
  10. Brûleur selon la revendication 1,
    caractérisé en ce que
    le canal d'afflux (10) fait partie d'une chambre de combustion annulaire (30).
EP99959164A 1998-12-23 1999-12-21 Bruleur pour generateur de chaleur Expired - Lifetime EP1141628B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19859829A DE19859829A1 (de) 1998-12-23 1998-12-23 Brenner zum Betrieb eines Wärmeerzeugers
DE19859829 1998-12-23
PCT/CH1999/000617 WO2000039503A1 (fr) 1998-12-23 1999-12-21 Bruleur pour generateur de chaleur

Publications (2)

Publication Number Publication Date
EP1141628A1 EP1141628A1 (fr) 2001-10-10
EP1141628B1 true EP1141628B1 (fr) 2005-05-18

Family

ID=7892510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99959164A Expired - Lifetime EP1141628B1 (fr) 1998-12-23 1999-12-21 Bruleur pour generateur de chaleur

Country Status (5)

Country Link
US (1) US6702574B1 (fr)
EP (1) EP1141628B1 (fr)
AU (1) AU1646000A (fr)
DE (2) DE19859829A1 (fr)
WO (1) WO2000039503A1 (fr)

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EP2253888B1 (fr) * 2009-05-14 2013-10-16 Alstom Technology Ltd Brûleur d'une turbine à gaz ayant un générateur de vortex avec une lance à combustible
US9243803B2 (en) 2011-10-06 2016-01-26 General Electric Company System for cooling a multi-tube fuel nozzle
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
EP2685161B1 (fr) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Agencement de chambre de combustion, en particulier pour turbine à gaz
EP2685163B1 (fr) * 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
JP5584260B2 (ja) * 2012-08-08 2014-09-03 日野自動車株式会社 排気浄化装置用バーナー
EP2885579B1 (fr) * 2012-08-16 2017-07-19 Services Pétroliers Schlumberger Brûleur à phases multiples à effet coanda à écrans
EP2722591A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz
US9534788B2 (en) * 2014-04-03 2017-01-03 General Electric Company Air fuel premixer for low emissions gas turbine combustor
USD842979S1 (en) * 2017-05-24 2019-03-12 Hamworthy Combustion Engineering Limited Atomizer
CN107514636B (zh) * 2017-10-10 2023-09-08 安徽科达洁能股份有限公司 一种悬浮焙烧炉用烧嘴及其应用
CN111750348B (zh) * 2020-06-04 2023-01-13 华帝股份有限公司 一种低噪音燃烧器及燃气热水器

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DE59710093D1 (de) * 1997-10-08 2003-06-18 Alstom Switzerland Ltd Verfahren zur Verbrennung von gasförmigen, flüssigen sowie mittel-oder niederkalorischen Brennstoffen in einem Brenner
ATE232282T1 (de) * 1997-11-25 2003-02-15 Alstom Brenner zum betrieb eines wärmeerzeugers

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DE59912077D1 (de) 2005-06-23
US6702574B1 (en) 2004-03-09
DE19859829A1 (de) 2000-06-29
AU1646000A (en) 2000-07-31
WO2000039503A1 (fr) 2000-07-06
EP1141628A1 (fr) 2001-10-10

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