EP0503319B1 - Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux - Google Patents

Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux Download PDF

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Publication number
EP0503319B1
EP0503319B1 EP92102736A EP92102736A EP0503319B1 EP 0503319 B1 EP0503319 B1 EP 0503319B1 EP 92102736 A EP92102736 A EP 92102736A EP 92102736 A EP92102736 A EP 92102736A EP 0503319 B1 EP0503319 B1 EP 0503319B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
nozzles
nozzle
interior
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
EP92102736A
Other languages
German (de)
English (en)
Other versions
EP0503319A2 (fr
EP0503319A3 (en
Inventor
Klaus Dr. Döbbeling
Thomas Dr. Sattelmayer
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 Asea Brown Boveri Ltd
ABB AB
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 EP0503319A2 publication Critical patent/EP0503319A2/fr
Publication of EP0503319A3 publication Critical patent/EP0503319A3/de
Application granted granted Critical
Publication of EP0503319B1 publication Critical patent/EP0503319B1/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
    • 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
    • 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
    • F23R3/286—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
    • 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
    • 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 burner for premix combustion of a liquid and / or gaseous fuel according to the preamble of claim 1.
  • a burner has become known, in the interior of which a fuel nozzle is placed, from which a conical fuel spray is formed which extends in the direction of flow and flows around combustion air flows flowing tangentially into the interior of the burner and is mixed down in the flow direction of the burner becomes.
  • the tangential inlet opening into the interior of the burner results from the fact that the burner itself consists of two hollow, conical partial bodies, the central axes of which are offset from one another.
  • the ignition of this air / fuel mixture takes place at the outlet of the burner, a backflow zone forming in the area of the burner mouth, which together with the high axial speed upstream prevents the flame from flashing back from the combustion chamber upstream into the burner.
  • the invention seeks to remedy this.
  • the object of the invention is to propose a low-emission, dry combustion of a liquid fuel in a burner of the type mentioned at the outset, the interaction between flame radiation and fuel droplets, which leads to pre-ignition of the mixture, must be prevented.
  • the main advantage of the invention is that the liquid fuel is injected into an area immediately before entering the interior and is mixed there with the combustion air flow.
  • the fuel is evaporated essentially only in the inlet openings of the burner, only fuel vapor enters the interior of the burner.
  • the risk of the mixture igniting prematurely is eliminated, since an evaporated fuel hardly absorbs flame radiation. This enables low-NOx / CO / UHC combustion.
  • FIGS. 1 and 2 In order to be able to grasp the structure of the burner better and immediately, it is advisable to use FIGS. 1 and 2 at the same time.
  • the core body of the burner shown in FIG. 1 consists of two half hollow, conical partial bodies 1, 2 which are offset from one another and thus form the body according to the application.
  • the displacement of the respective central axes 1a, 2a (see FIG. 2) of the individual partial bodies 1, 2 creates a tangential inlet opening 1b, 2b on both sides of the burner in an axially symmetrical arrangement, through which the inflow of an air / fuel mixture into the Interior 3 of the burner, ie flows into the cone cavity, the direction of flow of the air / fuel mixture through the 180 ° offset inlet openings 1b, 2b into the interior 3 in the clockwise or counterclockwise direction, depending on the plane in which the offset of the central axes 1a, 2a is determined.
  • the conical shape of the partial bodies 1, 2 shown in the direction of flow has a certain fixed angle.
  • the partial bodies 1, 2 can describe an increasing taper (convex shape) or a decreasing taper (concave shape) in the direction of flow.
  • the last two forms are not included in the drawing, as they can easily be traced. Which form is ultimately used depends on the various parameters of the combustion process. The form shown here in the drawing will preferably be used.
  • the tangential width of the inlet openings 1b, 2b is a measure that results from the offset of the two central axes 1a, 2a (see FIG. 2) with respect to one another.
  • the two tapered partial bodies 1, 2 can each have a cylindrical, not shown initial part, which, analogously to the partial bodies shown, run offset from one another, so that the tangential inlet openings 1b, 2b are present over the entire length of the respective burner.
  • the burner On the burner chamber side 16, the burner has a collar-shaped plate 11, which can form, for example, the inlet front of an annular combustion chamber or a furnace.
  • the plate 11 has a number of bores or openings 12 through which dilution air, combustion air, cooling air etc. can be fed to the front part of the combustion chamber 16.
  • This feed basically serves at least two purposes: first, a medium-like component can be achieved in the combustion chamber 16, second, this feed ensures that the flame front is stabilized in the direction of a compact structure.
  • a plurality of nozzles 9, 10 act along the inlet openings 1b, 2b to the interior 3 of the burner and draw the liquid fuel 5a from the central feed channel 5, 6 assigned to each inlet opening 1b, 2b via nozzle channels 7, 8.
  • the central supply ducts 5, 6 are placed upstream of the inlet openings 1b, 2b with respect to the combustion air flow 13.
  • the bridging between the feed line and the air / fuel mixing location along the inlet openings 1b, 2b is taken over by the nozzle channels 7, 8 already mentioned.
  • the number of nozzle channels 7, 8 essentially depends on the length and the power to be provided by the burner.
  • the liquid fuel is injected via the nozzles 9, 10 with a small spray cone angle in the longitudinal direction of the inlet openings 1b, 2b.
  • the nozzles on the extremities of the burner must face each other, i.e. the first nozzle at the burner inlet in the flow direction, the last nozzle at the burner mouth in the counterflow direction.
  • the nozzles in between bridge the spray cone spacing in both flow directions to the neighboring nozzles.
  • the nozzles acting in both directions have the reference symbol 9
  • the nozzles acting on the extremities of the burner have the reference symbol 10.
  • the nozzles can also be slightly inclined towards the burner axis, to increase the degree of mixing .
  • the structure of the nozzles can be simple, so they can easily be simple perforated nozzles, such as those found in diesel engine technology.
  • a high-pressure atomization nozzle with a turbulence chamber is preferably provided for the optimal atomization of a liquid fuel.
  • part of the available nozzle admission pressure is used to generate high levels of turbulence in the fluid to be atomized.
  • Turbulence generation is achieved by means of an abrupt expansion (Carnot diffuser) into the turbulence chamber located in front of the actual nozzle hole.
  • the resulting liquid fuel spray is characterized by small angles of spread, corresponding to the relatively small width of the inlet openings, and very small droplet sizes.
  • the fuel is evaporated essentially only in the area of the inlet openings 1b, 2b into the interior 3 of the burner, so that only one fuel vapor enters there.
  • the liquid fuel assigned very high pressures in the order of more than 100 bar. Furthermore, it is important that the nozzles are arranged in such a way that a uniform fuel vapor distribution is established along the inlet openings 1b, 2b and the surface of the adjacent walls is not wetted, in order to prevent the risk of coking in the course of the combustion.
  • operation with a gaseous fuel can also be provided, in which case the quality of the fuel evaporation can be easily achieved.
  • An additional central fuel nozzle 4 which is fed with a liquid and / or gaseous fuel 4a, is provided at the beginning of the burner and, if required, is intended to serve the combustion process with a limit fuel quantity which is predetermined at low thermal outputs and low fuel moments driving diffusion-like combustion; Then this fuel supply is then completely or at least, depending on the type of fuel, largely blocked.
  • This support will, however, be within a tolerance range that does not make the task-specific objectives of the subject matter impossible.
  • the air / fuel mixture 13 / 5a flowing into the interior 3 of the burner through the tangential inlet openings 1b, 2b forms, according to the geometric design of the burner, a conical mixture profile which winds in the direction of flow in a vortex.
  • the optimal, homogeneous fuel concentration is achieved over the cross section, so here in the area of the backflow zone 15 there is a very uniform fuel / air mixture.
  • the ignition itself takes place at the tip of the return flow zone 15: a stable flame front 14 can only arise at this point.
  • FIG. 2 is a section through the burner along a plane in the area of the middle nozzle channel 7.
  • the combustion air 13, depending on the fuel, must be coordinated in such a way that the fuel evaporation rate on which it is based can be achieved only in the area of the inlet openings 1b, 2b.
  • the combustion air 13 is an air / exhaust gas mixture: the recirculation of a certain amount of partially cooled exhaust gas proves to be advantageous not only when the burner is used in gas turbine groups, but also when the burner is used in atmospheric combustion plants with a near-stoichiometric driving style, ie when the ratio between recirculated exhaust gas and fresh air supplied is approximately 0.7.
  • a mixed temperature of the air / exhaust gas mixture which is now introduced instead of a pure fresh air flow, will be approximately 400 ° C.
  • these conditions lead, for example, to optimal evaporation conditions, correspondingly to a minimization of the NOx / CO / UHC emissions in the subsequent combustion process.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Claims (7)

  1. Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux, se composant essentiellement de corps partiels coniques creux (1, 2) placés l'un au-dessus de l'autre, dont les axes centraux (1a, 2a) sont orientés dans la direction longitudinale des corps partiels (1, 2) en étant décalés l'un par rapport à l'autre, de telle façon qu'il apparaisse, sur la longueur du brûleur, des ouvertures d'entrée tangentielles (1b, 2b) pour la pénétration d'un courant d'air de combustion (13) dans le volume intérieur (3) du brûleur, caractérisé en ce que, dans la région de chaque ouverture d'entrée (1b, 2b) est disposé au moins un gicleur (9, 10), en ce que le combustible (5a) peut être injecté par le gicleur en direction longitudinale des ouvertures d'entrée, essentiellement transversalement au courant d'air de combustion (13) qui entre dans le volume intérieur (3) du brûleur.
  2. Brûleur suivant la revendication 1, caractérisé en ce que, pour plusieurs gicleurs, les gicleurs (10) placés aux extrémités du brûleur injectent d'un côté et l'un vers l'autre, les gicleurs intermédiaires (9) injectent de l'un à l'autre.
  3. Brûleur suivant la revendication 1, caractérisé en ce que les gicleurs (9, 10) sont inclinés vers l'axe longitudinal du brûleur.
  4. Brûleur suivant la revendication 1, caractérisé en ce que les gicleurs (9, 10) sont alimentés à partir de canaux d'admission centraux (5, 6), qui sont placés au-dessus des ouvertures d'entrée (1b, 2b).
  5. Brûleur suivant la revendication 1, caractérisé en ce que les corps partiels (1, 2) présentent, dans la direction d'écoulement, un angle fixe, ou une conicité progressive ou une conicité dégressive.
  6. Brûleur suivant la revendication 1, caractérisé en ce qu'un gicleur supplémentaire (4) est placé au début du brûleur, par lequel un combustible liquide et/ou gazeux (4a) peut être injecté dans le volume intérieur (3) du brûleur.
  7. Brûleur suivant la revendication 1, caractérisé en ce que les corps partiels (1, 2) portent à leur extrémité une plaque (11) en forme de collerette, qui présente un certain nombre d'ouvertures (12).
EP92102736A 1991-03-12 1992-02-19 Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux Expired - Lifetime EP0503319B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH734/91 1991-03-12
CH734/91A CH682952A5 (de) 1991-03-12 1991-03-12 Brenner für eine Vormischverbrennung eines flüssigen und/oder gasförmigen Brennstoffes.

Publications (3)

Publication Number Publication Date
EP0503319A2 EP0503319A2 (fr) 1992-09-16
EP0503319A3 EP0503319A3 (en) 1993-02-24
EP0503319B1 true EP0503319B1 (fr) 1996-04-24

Family

ID=4193954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92102736A Expired - Lifetime EP0503319B1 (fr) 1991-03-12 1992-02-19 Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux

Country Status (6)

Country Link
US (1) US5244380A (fr)
EP (1) EP0503319B1 (fr)
JP (1) JPH04320711A (fr)
CA (1) CA2061746A1 (fr)
CH (1) CH682952A5 (fr)
DE (2) DE4113681A1 (fr)

Families Citing this family (32)

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Publication number Priority date Publication date Assignee Title
EP0592717B1 (fr) * 1992-10-16 1998-02-25 Asea Brown Boveri Ag Brûleur opérant au gaz du type à prémélange
DE4316474A1 (de) * 1993-05-17 1994-11-24 Abb Management Ag Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
DE4330083A1 (de) * 1993-09-06 1995-03-09 Abb Research Ltd Verfahren zum Betrieb eines Vormischbrenners
US5461865A (en) * 1994-02-24 1995-10-31 United Technologies Corporation Tangential entry fuel nozzle
DE4411623A1 (de) * 1994-04-02 1995-10-05 Abb Management Ag Vormischbrenner
DE4424599A1 (de) * 1994-07-13 1996-01-18 Abb Research Ltd Verfahren und Vorrichtung zum Betreiben eines kombinierten Brenners für flüssige und gasförmige Brennstoffe
DE4429757A1 (de) * 1994-08-22 1996-02-29 Abb Management Ag Brennkammer
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
DE4440558A1 (de) * 1994-11-12 1996-05-15 Abb Research Ltd Vormischbrenner
DE4441235A1 (de) * 1994-11-19 1996-05-23 Abb Management Ag Brennkammer mit Mehrstufenverbrennung
DE4445279A1 (de) * 1994-12-19 1996-06-20 Abb Management Ag Einspritzdüse
DE19626240A1 (de) * 1996-06-29 1998-01-02 Abb Research Ltd Vormischbrenner und Verfahren zum Betrieb des Brenners
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
SE514341C2 (sv) * 1998-06-18 2001-02-12 Abb Ab Förfarande för start av en brännaranordning till en gasturbin
EP0981016B1 (fr) * 1998-08-19 2004-01-07 ALSTOM (Switzerland) Ltd Brûleur pour le fonctionnement d'une chambre de combustion
DE19854382B4 (de) * 1998-11-25 2009-01-02 Alstom Verfahren und Vorrichtung zur Zerstäubung flüssigen Brennstoffs für eine Feuerungsanlage
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
AU2003226079A1 (en) * 2002-04-09 2003-10-27 Sapias, Inc. Asset management platform
US6623267B1 (en) 2002-12-31 2003-09-23 Tibbs M. Golladay, Jr. Industrial burner
US20040202977A1 (en) * 2003-04-08 2004-10-14 Ken Walkup Low NOx burner
US20050003316A1 (en) * 2003-05-31 2005-01-06 Eugene Showers Counterflow fuel injection nozzle in a burner-boiler system
WO2005121648A1 (fr) * 2004-06-08 2005-12-22 Alstom Technology Ltd Bruleur a premelange a alimentation etagee en combustible liquide et procede pour faire fonctionner un bruleur a premelange
DK1856442T3 (da) * 2005-03-09 2010-12-20 Alstom Technology Ltd Forblandingsbrænder til frembringelse af en antændelig brændstof-luftblanding
ATE480737T1 (de) * 2005-06-17 2010-09-15 Alstom Technology Ltd Brenner zur vormischartigen verbrennung
WO2009103671A1 (fr) * 2008-02-20 2009-08-27 Alstom Technology Ltd Turbine à gaz à architecture de refroidissement améliorée
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
DE102014205203B3 (de) * 2014-03-20 2015-05-21 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205198A1 (de) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Brenner und Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205201A1 (de) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205200B3 (de) 2014-03-20 2015-06-11 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
CN106287816B (zh) * 2016-08-12 2019-01-18 中国航空工业集团公司沈阳发动机设计研究所 一种干式低排放燃烧器
CN110195864A (zh) * 2018-06-04 2019-09-03 华帝股份有限公司 一种红外燃烧器

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US3890088A (en) * 1970-09-17 1975-06-17 Advanced Tech Lab Apparatus for reducing formation of oxides of nitrogen in combustion processes
US3834854A (en) * 1972-11-02 1974-09-10 Phillips Petroleum Co Method and apparatus for charging a burner
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JPS61153404A (ja) * 1984-12-27 1986-07-12 Babcock Hitachi Kk 触媒バ−ナ
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH680946A5 (fr) * 1989-12-19 1992-12-15 Asea Brown Boveri

Also Published As

Publication number Publication date
US5244380A (en) 1993-09-14
EP0503319A2 (fr) 1992-09-16
JPH04320711A (ja) 1992-11-11
DE4113681A1 (de) 1992-09-17
EP0503319A3 (en) 1993-02-24
DE59206081D1 (de) 1996-05-30
CH682952A5 (de) 1993-12-15
CA2061746A1 (fr) 1992-09-13

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