EP0433790B1 - Brûleur - Google Patents

Brûleur

Info

Publication number
EP0433790B1
EP0433790B1 EP90123495A EP90123495A EP0433790B1 EP 0433790 B1 EP0433790 B1 EP 0433790B1 EP 90123495 A EP90123495 A EP 90123495A EP 90123495 A EP90123495 A EP 90123495A EP 0433790 B1 EP0433790 B1 EP 0433790B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
injector
duct
inlet
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
EP90123495A
Other languages
German (de)
English (en)
Other versions
EP0433790A1 (fr
Inventor
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.)
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 EP0433790A1 publication Critical patent/EP0433790A1/fr
Application granted granted Critical
Publication of EP0433790B1 publication Critical patent/EP0433790B1/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
    • 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
    • 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 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
    • 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 a burner according to the preamble of claim 1. It also relates to a method for operating such a burner.
  • a burner is known from EP-A1-0 321 809, which consists of two half-hollow partial cone bodies which are offset from one another.
  • the cone shape of the partial cone body shown in the figure extends over a certain fixed angle in the flow direction.
  • the aforementioned displacement of the partial cone bodies relative to one another creates on both sides of the burner body a tangential entry slot over the entire length of the burner, the width of which corresponds to the respective offset of the central axes of the partial cone bodies to one another, and through which the combustion air flows into the interior of the burner.
  • a fuel nozzle is placed in the interior at the beginning of the burner, the fuel injection of which preferably starts in the center of the mutually offset central axes of the partial cone bodies. Further fuel nozzles are provided in the area of the tangential inlet slots. Liquid fuel is preferably supplied through the central fuel nozzle, while the fuel nozzles in the region of the tangential inlet slots are preferably operated with a gaseous fuel. If such a burner is now operated with a medium-calorific gas, which generally contains highly flammable hydrogen, there is a concrete risk that the combustion air that is brought in is present and mix this gas so strongly already in the entry area, at the point of their meeting, that the mixture may ignite prematurely.
  • a medium-calorific gas which generally contains highly flammable hydrogen
  • the invention seeks to remedy this.
  • the invention is based on the object of providing measures in a burner of the type mentioned at the outset which make it possible to ignite the mixture prematurely when a medium-calorific gas is used as fuel.
  • the measures should also enable the mixing process to be stabilized.
  • the main advantage of the invention is that the NO x emissions remain low because there is no premature ignition.
  • the injector which forms the solution according to the task, makes it possible not to significantly change the flow field of the burner used, despite the high mass flow share of the medium-calorific gas in the air / gas mixture.
  • This is achieved with the aid of a suitable distribution of a number of injector bores of the same size or with the aid of an arrangement of bores whose diameter varies in a suitable manner.
  • the Density of the gas inlet holes (P GB ) proportional to the radially averaged combustion air inlet speed through the tangential air inlet slots of the burner.
  • the injector according to the invention does not allow shear layers to arise during the mixing process: these shear layers, which always arise when the velocity of the gaseous fuel at the mixing location is greater than the air velocity, cause strong turbulence, which triggers instability in the system.
  • these shear layers which always arise when the velocity of the gaseous fuel at the mixing location is greater than the air velocity, cause strong turbulence, which triggers instability in the system.
  • the mixing process is designed for full load with regard to the flow rate of the gaseous fuel: the gaseous fuel is "breathed" into the air flow almost without pressure.
  • Another advantage of the invention can be seen in the fact that, in suitable temperature and pressure ranges, even combustion of gases with a low calorific value is conceivable.
  • FIGS. 1 and 2 should be used simultaneously. Furthermore, so that FIG. 1 remains clear, the injectors shown in FIG. 2 have not been included.
  • Fig. 1 shows a burner 1, which consists of two half, hollow partial cone bodies 2, 3, which are offset from one another.
  • the conical shape of the partial conical bodies 2, 3 shown has a certain fixed angle in the flow direction.
  • the partial cone bodies 2, 3 can have an increasing taper (convex shape) or a decreasing taper (concave shape) in the direction of flow.
  • the latter two forms are not recorded in the drawing, since they can be easily traced. Which form is ultimately used depends on the various parameters of the combustion process.
  • the form shown in the drawing is preferably used.
  • the offset of the respective central axis 2a, 3a see FIG.
  • the entry slot width S is a measure that results from the displacement of the two central axes 2a, 3a of the partial cone bodies 2, 3.
  • the two partial cone bodies 2, 3 each have a cylindrical initial part 2c, 3c, which, like the partial cone bodies 2, 3, also run offset from one another, so that the tangential entry slots 2b, 3b are present from the start.
  • the burner 1 can of course describe a purely conical shape, that is to say without a cylindrical starting body.
  • a nozzle is accommodated in this cylindrical starting body, which is preferably operated with a liquid fuel 5 and whose fuel injection 15 is preferably placed in the center of the two central axes 2a, 3a.
  • the two partial cone bodies 2, 3 each have a fuel line 10, 11, which are provided with openings 21 in the flow direction, which are distributed over the entire length of the fuel lines.
  • a gaseous fuel 6 is preferably introduced through the fuel lines 10, 11, this fuel being injected in the region of the tangential inlet slots 2b, 3b, as can be seen particularly well from FIG. 2.
  • the burner 1 also has a fuel supply, preferably a gaseous fuel 4, which takes place via injectors 12, 13, which also act in the region of the tangential inlet slots 2b, 3b via a number of gas bores 14, as can be seen comprehensively from FIG. 2.
  • a fuel supply preferably a gaseous fuel 4
  • FIG. 2 It is basically the case that the burner 1 can be operated via individual fuel feeds or through a mixed operation with the available fuel options.
  • the burner 1 On the combustion chamber side 22, the burner 1 has a collar-shaped wall 20, through which holes, not shown, are provided, through which dilution air or cooling air is supplied to the front part of the combustion chamber 22.
  • This fuel injection 15 can be an air-assisted atomization or a pressure atomization.
  • the conical liquid fuel profile 16 is enclosed by a trangentially flowing combustion air stream 8 and an axially brought in further air stream 7a. About the composition of the tangential inflowing air / fuel mixture 8 is discussed in more detail in the description of FIG. 2. In the axial direction of the burner 1, the concentration of the injected liquid fuel 5 is continuously reduced by an air flow or by the air / fuel mixture 8.
  • gaseous fuel 6 is used via the two fuel lines 10, 11, the mixture formation begins with the invisible air supply (see FIG. 2, item 7) directly in the region of the tangential inlet slots 2b, 3b, corresponding to the fuel openings 21 provided there
  • the combustion process of each air / fuel mixture then begins at the top of this backflow zone 18. Only at this point can a stable flame front 19 arise. A flashback of the flame inside the burner 1 like this With known premixing sections, there is always no need to worry, whereas complex flame holders are sought to remedy this situation.
  • the air used (see FIG. 2, item 7) is preheated at most, accelerated, holistic evaporation of the liquid fuel 5 occurs before the point at the outlet of the burner 1 is reached at which the combustion process of the mixture begins.
  • the degree of evaporation is dependent on the size of the burner 1, the drop size and the temperature of the air streams 7a, 7 respectively. of the air / fuel mixture 8 dependent.
  • the nitrogen oxide and carbon monoxide emissions are low if the excess air is at least 60%, which means an additional one precaution to minimize NOx emissions is available.
  • the geometrically fixed return flow zone 18 is inherently position-stable, because the swirl number increases in the direction of flow in the region of the cone shape of the burner 1.
  • the axial speed leaves further influence each other by axially feeding the already mentioned air flow 7a.
  • the design of the burner 1 is ideally suited, given a given overall length of a burner 1, to adapt the size of the tangential entry slots 2b, 3b to the requirements by pushing the partial cone bodies 2, 3 towards or away from one another, as a result of which the distance between the two central axes 2a, 3a reduced or increases, and accordingly the entry slot width S also changes, as can be seen particularly well from FIG. 2.
  • the partial cone bodies 2, 3 can also be moved relative to one another in another plane. Seen in this way, the burner 1 can be individually adapted without changing its focal length.
  • the injector 12, 13 is designed in such a way that the gaseous fuel 4, which is preferably used, flows from a gas supply pipe 12a, 13a through which a gas can flow, via a number of gas bores 14, into a gas injector channel (injection channel) 12b, 13b. This extends into the area of the tangential entry slot 2b, 3b.
  • the width of the injector 12, 13 is designed such that the air 7 that is brought in flows along the flanks of the injector 12, 13 and begins to mix with the gaseous fuel 4 in the region of the tangential inlet slot 2b, 3b, whereupon the air / Fuel mixture 8 is formed.
  • the property of the injector 12, 13 of not significantly changing the flow field of the burner 1 despite the high mass flow portion of the medium-calorific gas used in the air / gas mixture. This is achieved with the help of a suitable distribution of the gas holes 14 of the same size or with the help an arrangement of holes, the diameter of which varies in a suitable manner.
  • the density of the gas holes is proportional to the radially averaged speed of the air 7 in the inlet slots 2b, 3b of the burner 1, and follows the following formula: where ⁇ is the opening angle of the burner 1 (see FIG. 1), S denotes the entry slot width and R is the mean radius of the position of the entry slot 2b, 3b in question (see FIG. 1).
  • the directions of the gas bores 14 should preferably coincide with the prevailing flow direction in the inlet slot 2b, 3b. It is important that the gaseous fuel 4 undergoes the actual throttling when it enters the gas bores 14 from the gas supply channel 12a, 13a.
  • the gas holes 14 are to be designed in such a way that they cannot be freely blown into the interior 17 of the burner 1. These gas holes 14 open into a gas injector channel 12b, 13b, which extends as far as the inlet slot 2b, 3b. It is advantageous if this channel is divided several times in the longitudinal direction by flow plates that cannot be seen, so that the gaseous fuel 4 is channeled in the direction of the combustion air flow under design conditions, for example full load. Furthermore, aid is provided that the gaseous fuel 4 blows at the respective speed of the air 7 brought in in the area of the inlet slots 2b, 3b.
  • the transition from the gas holes 14 to the subsequent gas injector channels 12b, 13b is preferably designed as a Borda-Carnot extension.
  • the minimum length of the gas injector channel is concerned, the usual rule of 3-5 hydraulic diameters resp. 6 - 10 gap width used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Control Of Combustion (AREA)
  • Manufacture, Treatment Of Glass Fibers (AREA)

Claims (6)

  1. Brûleur, se composant essentiellement d'au moins deux corps partiellement coniques placés l'un sur l'autre avec une forme conique s'ouvrant dans le sens de l'écoulement, dans lequel les axes centraux de ces corps partiellement coniques sont décalés en direction longitudinale l'un par rapport à l'autre de telle façon qu'il se forme sur la longueur du brûleur des fentes d'entrée tangentielles vers l'espace intérieur du brûleur, d'un gicleur pour l'introduction de combustible liquide, d'une conduite de combustible pour l'injection de combustible gazeux dans la région des fentes d'entrée tangentielles et d'un canal pour l'entrée d'air de combustion, caractérisé en ce que dans le canal (23, 24) est placé un injecteur (12, 13) pour un autre combustible gazeux (4), qui s'écoule hors de l'injecteur (12, 13) dans la région des fentes d'entrée tangentielles (2b, 3b) et peut s'y mélanger avec le courant d'air (7) circulant à travers le canal (23, 24).
  2. Brûleur suivant la revendication 1, caractérisé en ce que l'injecteur (12, 13) se compose d'un canal d'arrivée (12a, 13a) pour le combustible (4) s'étendant dans le sens de l'écoulement du brûleur (1), en ce que le canal d'arrivée (12a, 13a) présente dans le sens d'écoulement du combustible (4) un certain nombre de trous (14), en ce que les trous (14) débouchent dans un canal d'injecteur (12b, 13b) s'étendant jusque dans la région de la fente d'entrée (2b, 3b).
  3. Brûleur suivant la revendication 2, caractérisé en ce que le passage des trous (14) au canal d'injecteur (12b, 13b) qui suit est formé par un évasement de Borda-Carnot.
  4. Brûleur suivant la revendication 2, caractérisé en ce que le nombre (ρGB) des trous (14) par unité de surface est proportionnel à la vitesse radiale moyenne d'entrée de l'air (7) dans la région de la fente d'entrée (2b, 3b) du brûleur (1), suivant la relation suivante :
    Figure imgb0004
     dans laquelle α est l'angle d'ouverture du brûleur conique (1), S désigne la largeur des fentes d'entrée et R désigne le rayon moyen de l'endroit respectivement considéré de la fente d'entrée (2b, 3b).
  5. Brûleur suivant la revendication 2, caractérisé en ce que des auxiliaires d'écoulement pour le combustible (4) sont prévus dans le canal d'injecteur (12b, 13b) pour une adaptation à la direction d'écoulement du courant d'air (7) et de l'air de combustion (8).
  6. Procédé de conduite d'un brûleur suivant la revendication 1, caractérisé en ce que la vitesse d'entrée du combustible gazeux (4) dans l'espace intérieur (17) du brûleur (1) est égale ou inférieure à la vitesse du courant d'air (7) sortant du canal (23, 24).
EP90123495A 1989-12-22 1990-12-07 Brûleur Expired - Lifetime EP0433790B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4602/89A CH680467A5 (fr) 1989-12-22 1989-12-22
CH4602/89 1989-12-22

Publications (2)

Publication Number Publication Date
EP0433790A1 EP0433790A1 (fr) 1991-06-26
EP0433790B1 true EP0433790B1 (fr) 1995-03-08

Family

ID=4279159

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90123495A Expired - Lifetime EP0433790B1 (fr) 1989-12-22 1990-12-07 Brûleur

Country Status (9)

Country Link
US (1) US5169302A (fr)
EP (1) EP0433790B1 (fr)
JP (1) JP3011775B2 (fr)
AT (1) ATE119650T1 (fr)
CA (1) CA2032562A1 (fr)
CH (1) CH680467A5 (fr)
DE (1) DE59008639D1 (fr)
PL (1) PL288225A1 (fr)
RU (1) RU2011117C1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993017279A1 (fr) * 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange
EP0641971A2 (fr) * 1993-09-06 1995-03-08 Abb Research Ltd. Procédé pour commander un brûleur à prémélange
EP0683219A2 (fr) * 1994-05-19 1995-11-22 Abb Research Ltd. Procédé de gazéification de combustibles carbonés à l'aide d'air soufflé
US5588824A (en) * 1994-12-19 1996-12-31 Abb Management Ag Injection nozzle
US5588826A (en) * 1994-10-01 1996-12-31 Abb Management Ag Burner
US5645410A (en) * 1994-11-19 1997-07-08 Asea Brown Boveri Ag Combustion chamber with multi-stage combustion
US5674066A (en) * 1995-01-30 1997-10-07 Asea Brown Boveri Ag Burner
US6390805B1 (en) 1998-09-16 2002-05-21 Asea Brown Boveri Ag Method of preventing flow instabilities in a burner
EP1262714A1 (fr) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
US8801429B2 (en) 2006-03-30 2014-08-12 Alstom Technology Ltd Burner arrangement

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DE59208364D1 (de) * 1992-10-23 1997-05-22 Asea Brown Boveri Brenner mit elektrischer Zündeinrichtung
DE4242003A1 (de) * 1992-12-12 1994-06-16 Abb Research Ltd Prozesswärmeerzeuger
DE4242721A1 (de) * 1992-12-17 1994-06-23 Asea Brown Boveri Gasturbinenbrennkammer
DE4302847A1 (de) * 1993-02-02 1994-08-04 Abb Research Ltd Verfahren zur schadstoffarmen 2-Stufen-Verbrennung eines Brennstoffs sowie Vorrichtung zur Durchführung des Verfahrens
DE4304213A1 (de) * 1993-02-12 1994-08-18 Abb Research Ltd Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
US5461865A (en) * 1994-02-24 1995-10-31 United Technologies Corporation Tangential entry fuel nozzle
DE4440558A1 (de) * 1994-11-12 1996-05-15 Abb Research Ltd Vormischbrenner
EP0918191B1 (fr) * 1997-11-21 2003-07-02 Alstom Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6464489B1 (en) * 1997-11-24 2002-10-15 Alstom Method and apparatus for controlling thermoacoustic vibrations in a combustion system
US6176087B1 (en) 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
US6113078A (en) * 1998-03-18 2000-09-05 Lytesyde, Llc Fluid processing method
US6141954A (en) * 1998-05-18 2000-11-07 United Technologies Corporation Premixing fuel injector with improved flame disgorgement capacity
DE59810551D1 (de) * 1998-08-19 2004-02-12 Alstom Switzerland Ltd Brenner zum Betrieb einer Brennkammer
EP0985876A1 (fr) * 1998-09-10 2000-03-15 Abb Research Ltd. Brûleur
DE59812039D1 (de) 1998-11-18 2004-11-04 Alstom Technology Ltd Baden Brenner
DE10000415A1 (de) * 2000-01-07 2001-09-06 Alstom Power Schweiz Ag Baden Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
AU2001272682A1 (en) * 2000-06-15 2001-12-24 Alstom Power N.V. Method for operating a burner and burner with stepped premix gas injection
GB2368386A (en) 2000-10-23 2002-05-01 Alstom Power Nv Gas turbine engine combustion system
JP3940705B2 (ja) * 2003-06-19 2007-07-04 株式会社日立製作所 ガスタービン燃焼器及びその燃料供給方法
US7104528B2 (en) * 2003-08-15 2006-09-12 Lytesyde, Llc Fuel processor apparatus and method
DE112004002704B4 (de) * 2004-03-03 2011-04-07 Mitsubishi Heavy Industries, Ltd. Verbrennungsanlage
EP1614967B1 (fr) * 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
JP4509742B2 (ja) * 2004-11-04 2010-07-21 株式会社日立製作所 ガスタービン発電設備
DE102005015152A1 (de) 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer
ES2352679T3 (es) * 2005-06-17 2011-02-22 Alstom Technology Ltd Quemador para combustión de premezcla.
US7717096B2 (en) * 2006-01-23 2010-05-18 Lytesyde, Llc Fuel processor apparatus and method
US7681569B2 (en) * 2006-01-23 2010-03-23 Lytesyde, Llc Medical liquid processor apparatus and method
JP4571612B2 (ja) * 2006-12-11 2010-10-27 株式会社日立製作所 ガスタービン燃焼器及びその燃料供給方法
US8028674B2 (en) * 2007-08-07 2011-10-04 Lytesyde, Llc Fuel processor apparatus and method
CN101504140B (zh) * 2008-02-04 2011-05-11 林光湧 低排放高效节能燃烧器
US20090249789A1 (en) * 2008-04-08 2009-10-08 Baifang Zuo Burner tube premixer and method for mixing air and gas in a gas turbine engine
CN107255278B (zh) * 2017-07-21 2019-04-05 东北大学 一种切缝旋流低氮氧化物燃烧器

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US4175920A (en) * 1975-07-31 1979-11-27 Exxon Research & Engineering Co. Multiple fuel supply system for staged air burners
EP0210462B1 (fr) * 1985-07-30 1989-03-15 BBC Brown Boveri AG Chambre de combustion double
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993017279A1 (fr) * 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange
EP0641971A2 (fr) * 1993-09-06 1995-03-08 Abb Research Ltd. Procédé pour commander un brûleur à prémélange
EP0683219A2 (fr) * 1994-05-19 1995-11-22 Abb Research Ltd. Procédé de gazéification de combustibles carbonés à l'aide d'air soufflé
US5588826A (en) * 1994-10-01 1996-12-31 Abb Management Ag Burner
US5645410A (en) * 1994-11-19 1997-07-08 Asea Brown Boveri Ag Combustion chamber with multi-stage combustion
US5588824A (en) * 1994-12-19 1996-12-31 Abb Management Ag Injection nozzle
US5674066A (en) * 1995-01-30 1997-10-07 Asea Brown Boveri Ag Burner
US6390805B1 (en) 1998-09-16 2002-05-21 Asea Brown Boveri Ag Method of preventing flow instabilities in a burner
EP1262714A1 (fr) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
US6672863B2 (en) 2001-06-01 2004-01-06 Alstom Technology Ltd Burner with exhaust gas recirculation
US8801429B2 (en) 2006-03-30 2014-08-12 Alstom Technology Ltd Burner arrangement

Also Published As

Publication number Publication date
RU2011117C1 (ru) 1994-04-15
JPH04136606A (ja) 1992-05-11
DE59008639D1 (de) 1995-04-13
EP0433790A1 (fr) 1991-06-26
CH680467A5 (fr) 1992-08-31
PL288225A1 (en) 1991-12-16
CA2032562A1 (fr) 1991-06-23
JP3011775B2 (ja) 2000-02-21
ATE119650T1 (de) 1995-03-15
US5169302A (en) 1992-12-08

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