EP0918190A1 - Brûleur pour la mise en oeuvre d'un générateur de chaleur - Google Patents

Brûleur pour la mise en oeuvre d'un générateur de chaleur Download PDF

Info

Publication number
EP0918190A1
EP0918190A1 EP97810892A EP97810892A EP0918190A1 EP 0918190 A1 EP0918190 A1 EP 0918190A1 EP 97810892 A EP97810892 A EP 97810892A EP 97810892 A EP97810892 A EP 97810892A EP 0918190 A1 EP0918190 A1 EP 0918190A1
Authority
EP
European Patent Office
Prior art keywords
flow
burner
burner according
mixing tube
section
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.)
Withdrawn
Application number
EP97810892A
Other languages
German (de)
English (en)
Inventor
Hanspeter Knöpfel
Thomas Ruck
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.)
Alstom SA
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to EP97810892A priority Critical patent/EP0918190A1/fr
Priority to US09/192,512 priority patent/US6019596A/en
Publication of EP0918190A1 publication Critical patent/EP0918190A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C15/00—Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass
    • 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
    • F23C7/02—Disposition of air supply not passing through burner
    • F23C7/06—Disposition of air supply not passing through burner for heating the incoming air
    • 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
    • F23D14/02—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
    • 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
    • F23D14/78—Cooling burner parts
    • 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
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Definitions

  • the invention relates to a burner for operating a heat generator according to Preamble of claim 1.
  • the upstream side consists of a swirl generator, the flow formed therein seamlessly in a mixing section is transferred. This is done using one at the beginning of the Mixing section flow geometry formed for this purpose, which consists of transition channels exists, which is sectoral, according to the number of those acting Partial body of the swirl generator, capture the end face of the mixing section and in Flow direction swirl. Downstream of these transition channels the mixing section has a number of filming holes, which one Ensure an increase in the flow velocity along the pipe wall. This is followed by a combustion chamber, the transition between the Mixing section and the combustion chamber formed by a cross-sectional jump in whose plane a backflow zone or backflow bubble forms.
  • the swirl strength in the swirl generator is selected so that the bursting of the vortex does not occur within the mixing section, but further downstream, as executed above, in the area of the cross-sectional jump.
  • the length of the mixing section is dimensioned so that a sufficient mixture quality for the Use of limited fuel types is guaranteed.
  • the invention seeks to remedy this.
  • the invention as set out in the claims is characterized, the task is based on a burner at the beginning to propose the above-mentioned type of precautions which have the disadvantages mentioned above is able to remedy, i.e.
  • the object of the invention is to minimize the Achieve pollutant emissions, especially NOx emissions.
  • the burner front cooling air used should not be discharged directly into the combustion chamber, but returned and to be admixed as film air to the main flow within the burner.
  • This amount of cooling air is initially preferably carried out using impingement cooling cooling the front wall of the burner before then in the above sense is returned.
  • the main advantages of the invention are the fact that the cooling air here at the same time the film air for the inner wall of the burner, respectively. corresponds to the mixing section, with which an increase of the Flow rate induce a flashback from the Combustion chamber permanently prevented upstream.
  • the same Burner output i.e. with the same fuel mass flow, more air for the Provided premix, with which a leaner mixture and thus deeper NOx emissions can be achieved.
  • Fig. 1 shows the overall structure of a burner.
  • a swirl generator 100 effective, the design of which is shown in more detail in the following FIGS. 3-6 is shown and described.
  • This swirl generator 100 is a cone-shaped structure that tangentially inflows several times from a tangentially Combustion air flow 115 is applied.
  • the one forming here Flow is based on a transition geometry provided downstream of the swirl generator 100 transitioned seamlessly into a transition piece 200, that no separation areas can occur there.
  • the configuration of this transition geometry is described in more detail in Fig. 6.
  • This transition piece 200 is extended on the outflow side of the transition geometry by a mixing tube 20, wherein both parts form the actual mixing section 220.
  • the mixing section 220 may consist of a single piece, i.e. then that the transition piece 200 and the mixing tube 20 into one contiguous structures merge, but the characteristics of one of every part. Become transition piece 200 and mixing tube 20 created from two parts, they are connected by a bushing ring 10, the same bushing ring 10 on the head side as anchoring surface for the swirl generator 100 serves. Such a bushing ring 10 also has the advantage that different mixing tubes can be used. Downstream side of the Mixing tube 20 is the actual combustion chamber 30 of a combustion chamber, which is only symbolized here by a flame tube.
  • the mixing section 220 largely fulfills the task that a downstream of the swirl generator 100 defined route is provided, in which a perfect premix of Different types of fuels can be achieved.
  • This mixing section so ostensibly the mixing tube 20, furthermore enables lossless flow guidance, so that it is also in operative connection with the transition geometry initially cannot form a backflow zone or backflow bubble, with what the length of the mixing section 220 to the quality of the mixture for all types of fuel Influence can be exercised.
  • this mixing section 220 has another one Property, which is that in it the axial velocity profile has a pronounced maximum on the axis, so that backfire the flame from the combustion chamber is not possible. However, it is correct that with such a configuration this axial velocity towards the wall falls off.
  • the mixing tube 20 in the flow and circumferential direction with a number regularly or irregularly distributed holes 21 of different cross-sections and directions provided through which an amount of air into the interior of the mixing tube 20th flows, and along the wall in the sense of a filming an increase in Induce flow rate.
  • These holes 21 can also be so be designed that at least on the inner wall of the mixing tube 20 additionally sets an effusion cooling. About feeding these holes 21 with air is discussed in more detail below.
  • Another option an increase in the speed of the mixture within the mixing tube To achieve 20 is that its flow cross-section on the outflow side of the transition channels 201, which have the transition geometry already mentioned form, undergoes a narrowing, reducing the overall speed level is raised within the mixing tube 20.
  • the bores 21 run at an acute angle with respect to the burner axis 60.
  • Other courses of these holes 21 are also possible.
  • the transition channels 201 thus bridge the respective cross-sectional difference, without negatively affecting the flow formed to influence. If the chosen precaution when guiding the pipe flow 40 along the mixing tube 20 an intolerable pressure loss triggers, this can be remedied by ending this Mixing tube 20, a diffuser, not shown in the figure, is provided.
  • combustion chamber 30 combustion chamber
  • a cooling system becomes concentric with the mixing tube 20 in the area of its outlet 300 provided.
  • This consists of an outer annular chamber 302, in which flows in a cooling air quantity 301.
  • This annular chamber 302 also closes a perforated plate 303, the holes provided here designed so are that the air flow 304 flowing through there impingement cooling to a bottom plate 305 spaced from perforated plate 303.
  • This bottom plate 305 as the front wall of the burner has the function of a heat protection plate compared to the calorific load from the combustion chamber 30, so that this Impact cooling must be extremely efficient here.
  • the cooling air which is calorically enriched by the impingement cooling, then flows through the holes 21 already mentioned in the interior of the mixing tube 20 and it then acts as film air along the inner wall.
  • This filmmaking increases the flow rate of those flowing through the mixing tube 20 Main flow 40, which has a positive effect against a flashback, and further contributes to the fact that more air with the same burner output can be provided for the premix, which means a leaner mixture arises and thus lower NOx emissions can be achieved.
  • Fig. 2 shows a schematic view of the burner according to Fig. 1, here in particular the flushing of a centrally arranged fuel nozzle 103 and the effect of fuel injectors 170 is pointed out.
  • the mode of action the remaining main components of the burner, namely swirl generator 100 and transition piece 200 are closer under the following figures described.
  • the fuel nozzle 103 is spaced with a ring 190 encased in which a number of circumferentially bored holes 161 through which an amount of air 160 is placed in an annular chamber 180 flows and performs the washing around the fuel nozzle 103.
  • These holes 161 are slanted forward so that it is appropriate axial component arises on the burner axis 60.
  • FIG. 4 is used at the same time as FIG. 3.
  • 3 is referred to the other figures as necessary in the description of FIG.
  • the first part of the burner according to FIG. 1 forms the swirl generator shown in FIG. 3 100.
  • This consists of two hollow conical partial bodies 101, 102, which are nested in a staggered manner.
  • the number of conical Partial body can of course be larger than two, like the figures 5 and 6 show; this depends in each case, as will be explained in more detail below will depend on the operating mode of the entire burner. It is with certain Operating constellations are not excluded, one from a single spiral to provide existing swirl generator.
  • the offset of the respective central axis or longitudinal symmetry axes 101b, 102b (cf. FIG. 4) of the conical partial bodies 101, 102 creates each other in the adjacent wall, in mirror image Arrangement, each a tangential inflow channel, i.e.
  • the conical shape of the partial bodies 101, 102 shown in the flow direction has one certain fixed angle. Of course, depending on the operational use, you can the partial bodies 101, 102 are increasing or decreasing in the direction of flow Show cone inclination, similar to a trumpet. Tulip. The latter two Shapes are not recorded in the drawing, as they are without for the specialist are further sensitive.
  • the two conical partial bodies 101, 102 each have a cylindrical annular start portion 101a. In the area of this cylindrical Initially, the fuel nozzle 103 already mentioned under FIG.
  • the conical Sub-bodies 101, 102 also each have a fuel line 108, 109, which are arranged along the tangential air inlet slots 119, 120 and are provided with injection openings 117, through which preferably a gaseous fuel 113 is injected into the combustion air 115 flowing through there is how the arrows 116 symbolize this.
  • These fuel lines 108, 109 are preferably at the latest at the end of the tangential inflow, arranged before entering the cone cavity 114, this by an optimal Obtain air / fuel mixture.
  • the fuel 112 introduced is normally one liquid fuel, forming a mixture with another medium, for example with a recirculated flue gas, is easily possible.
  • This fuel 112 is preferably at a very acute angle in the Cone cavity 114 injected.
  • the fuel nozzle 103 thus forms tapered fuel spray 105, which from the tangentially flowing rotating Combustion air 115 is enclosed and broken down.
  • the construction of the Swirl generator 100 is also particularly suitable, the size of the tangential Air inlet slots 119, 120 to change, so without changing the overall length of the swirl generator 100 covers a relatively large operational bandwidth can be.
  • the partial bodies 101, 102 are also in another Plane can be shifted towards each other, which even overlaps them can be provided. It is also possible to use the partial bodies 101, 102 can be nested spirally in one another by a counter-rotating movement.
  • FIG. 4 shows, among other things, the geometric configuration of optional ones Baffles 121a, 121b. They have a flow initiation function which, according to their length, the respective end of the tapered Partial bodies 101, 102 in the flow direction with respect to the combustion air 115 extend.
  • the channeling of the combustion air 115 into the cone cavity 114 can be opened or closed by one of the baffles 121a, 121b Area of entry of this channel into the fulcrum 114 placed cone cavity 123 can be optimized, especially if the original Gap size of the tangential air inlet slots 119, 120 changed dynamically should be, for example, to change the speed of the combustion air 115 to achieve.
  • these can be dynamic Precautions can also be provided statically by using baffles as needed form a fixed component with the conical partial bodies 101, 102.
  • the swirl generator 100 now consists of four partial bodies 130, 131, 132, 133 is constructed.
  • the associated longitudinal symmetry axes for each sub-body are marked with the letter a. To this Configuration is to be said that it is due to the lower generated with it Twist strength and in cooperation with a correspondingly enlarged Slot width is best suited, the bursting of the vortex flow on the downstream side to prevent the swirl generator in the mixing tube, thus causing the mixing tube to can fulfill the intended role.
  • FIG. 6 differs from FIG. 5 in that the partial bodies 140 here 141, 142, 143 have a blade profile shape which is used to provide a certain Flow is provided. Otherwise, the mode of operation of the swirl generator stayed the same.
  • the admixture of fuel 116 in the combustion air flow 115 happens from inside the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades.
  • the transition geometry is corresponding for a swirl generator 100 with four partial bodies 5 or 6, built. Accordingly, the transition geometry as a natural extension of the upstream partial bodies, four transition channels 201 on, whereby the conical quarter area of said partial body is extended until it cuts the wall of the mixing tube.
  • the same considerations also apply if the swirl generator is based on a principle other than the one below Fig. 3 described, is constructed.
  • the down in the direction of flow running surface of the individual transition channels 201 has a flow direction spiral shape, which has a crescent shape Course describes, corresponding to the fact that the flow cross-section is present of the transition piece 200 flared in the flow direction.
  • the swirl angle of the transition channels 201 in the flow direction is selected so that that the pipe flow then up to the cross-sectional jump on Combustion chamber entrance still has a sufficient distance to be perfect Premix with the injected fuel. Further increases the axial speed is also affected by the above-mentioned measures on the mixing tube wall downstream of the swirl generator.
  • the transition geometry and the measures in the area of the mixing tube bring about a significant increase of the axial velocity profile towards the center of the mixing tube, see above that the danger of early ignition is decisively counteracted.
  • the flow cross section of the tube 20 receives one in this area Transition radius R, the size of which basically depends on the flow within of the tube 20 depends.
  • This radius R is chosen so that the Applies flow to the wall and so the swirl number increases sharply.
  • the size of the radius R can be defined so that it is> 10% of the inside diameter d of the tube is 20.
  • the backflow bladder 50 increases enormously.
  • This radius R runs to the exit plane of the tube 20, the angle ⁇ between the beginning and end of curvature is ⁇ 90 °.
EP97810892A 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur Withdrawn EP0918190A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP97810892A EP0918190A1 (fr) 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur
US09/192,512 US6019596A (en) 1997-11-21 1998-11-17 Burner for operating a heat generator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810892A EP0918190A1 (fr) 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Publications (1)

Publication Number Publication Date
EP0918190A1 true EP0918190A1 (fr) 1999-05-26

Family

ID=8230483

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810892A Withdrawn EP0918190A1 (fr) 1997-11-21 1997-11-21 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Country Status (2)

Country Link
US (1) US6019596A (fr)
EP (1) EP0918190A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1070915A1 (fr) * 1999-07-22 2001-01-24 Asea Brown Boveri AG Brûleur à prémélange
EP1070914A1 (fr) * 1999-07-22 2001-01-24 ABB Alstom Power (Schweiz) AG Brûleur à prémélange
WO2002029318A1 (fr) * 2000-10-05 2002-04-11 Alstom (Switzerland) Ltd Procede et dispositif pour alimenter un bruleur a melange prealable en combustible
WO2009109452A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
US7871262B2 (en) * 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
CH703657A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Verfahren zum betrieb einer brenneranordnung sowie brenneranordnung zur durchführung des verfahrens.
US8459985B2 (en) 2008-03-07 2013-06-11 Alstom Technology Ltd Method and burner arrangement for the production of hot gas, and use of said method

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
US6360776B1 (en) 2000-11-01 2002-03-26 Rolls-Royce Corporation Apparatus for premixing in a gas turbine engine
DE10064259B4 (de) * 2000-12-22 2012-02-02 Alstom Technology Ltd. Brenner mit hoher Flammenstabilität
EP1262714A1 (fr) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
ITMI20012781A1 (it) * 2001-12-21 2003-06-21 Nuovo Pignone Spa Assieme migliorato di camera di pre miscelamento e di camera di combustione, a basse emissioni inquinanti per turbine a gas con combustibile
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
EP1342952A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement d'un brûleur et turbine à gaz
US6889523B2 (en) * 2003-03-07 2005-05-10 Elkcorp LNG production in cryogenic natural gas processing plants
US7007477B2 (en) * 2004-06-03 2006-03-07 General Electric Company Premixing burner with impingement cooled centerbody and method of cooling centerbody
JP2008519237A (ja) * 2004-11-03 2008-06-05 アルストム テクノロジー リミテッド 予混合バーナ
US7430851B2 (en) * 2005-01-18 2008-10-07 Parker-Hannifin Corporation Air and fuel venting device for fuel injector nozzle tip
DE102008000050A1 (de) * 2007-08-07 2009-02-12 Alstom Technology Ltd. Brenner für eine Brennkammer einer Turbogruppe
US8147121B2 (en) * 2008-07-09 2012-04-03 General Electric Company Pre-mixing apparatus for a turbine engine
US8112999B2 (en) * 2008-08-05 2012-02-14 General Electric Company Turbomachine injection nozzle including a coolant delivery system
US7886991B2 (en) * 2008-10-03 2011-02-15 General Electric Company Premixed direct injection nozzle
US8312722B2 (en) * 2008-10-23 2012-11-20 General Electric Company Flame holding tolerant fuel and air premixer for a gas turbine combustor
US8297059B2 (en) * 2009-01-22 2012-10-30 General Electric Company Nozzle for a turbomachine
US9140454B2 (en) * 2009-01-23 2015-09-22 General Electric Company Bundled multi-tube nozzle for a turbomachine
US8539773B2 (en) * 2009-02-04 2013-09-24 General Electric Company Premixed direct injection nozzle for highly reactive fuels
FR2945854B1 (fr) * 2009-05-19 2015-08-07 Snecma Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant
US9267690B2 (en) 2012-05-29 2016-02-23 General Electric Company Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same
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
EP2722591A1 (fr) * 2012-10-22 2014-04-23 Alstom Technology Ltd Brûleur à multiples cones pour une turbine à gaz
US10281140B2 (en) 2014-07-15 2019-05-07 Chevron U.S.A. Inc. Low NOx combustion method and apparatus
EP3617599A1 (fr) * 2018-09-03 2020-03-04 Siemens Aktiengesellschaft Brûleur à mélange air-carburant amélioré

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3033988A1 (de) * 1980-09-10 1982-03-18 Karl-Friedrich Dipl.-Wirtsch.-Ing. Dipl.-Ing. 5650 Solingen Schmid Gasbrenner zur erzeugung von heizgasen mit breiter temperaturvarianz
DE3901232A1 (de) * 1988-02-06 1989-08-17 Rolls Royce Plc Brenner fuer ein gasturbinentriebwerk
WO1995022033A1 (fr) * 1994-02-10 1995-08-17 Solar Turbines Incorporated Injecteur a temperature de buse faible
US5444982A (en) * 1994-01-12 1995-08-29 General Electric Company Cyclonic prechamber with a centerbody
EP0670456A1 (fr) * 1994-03-04 1995-09-06 NUOVOPIGNONE INDUSTRIE MECCANICHE E FONDERIA S.p.A. Système de combustion perfectionné à pollution réduite pour turbine à gaz
EP0751345A1 (fr) * 1991-12-24 1997-01-02 Kabushiki Kaisha Toshiba Ensemble à gicleur d'injection de carburant à utiliser dans une chambre de combustion de turbine à gaz
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3859786A (en) * 1972-05-25 1975-01-14 Ford Motor Co Combustor
JPS5129726A (fr) * 1974-09-06 1976-03-13 Mitsubishi Heavy Ind Ltd
US5013236A (en) * 1989-05-22 1991-05-07 Institute Of Gas Technology Ultra-low pollutant emission combustion process and apparatus
DE4424599A1 (de) * 1994-07-13 1996-01-18 Abb Research Ltd Verfahren und Vorrichtung zum Betreiben eines kombinierten Brenners für flüssige und gasförmige Brennstoffe
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
DE4441235A1 (de) * 1994-11-19 1996-05-23 Abb Management Ag Brennkammer mit Mehrstufenverbrennung
DE19523094A1 (de) * 1995-06-26 1997-01-02 Abb Management Ag Brennkammer
DE19618856B4 (de) * 1996-05-10 2006-04-13 Alstom Vorrichtung zum Betreiben einer mit kombinierten Brennern für flüssige und gasförmige Brennstoffe bestückten Ringbrennkammer

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3033988A1 (de) * 1980-09-10 1982-03-18 Karl-Friedrich Dipl.-Wirtsch.-Ing. Dipl.-Ing. 5650 Solingen Schmid Gasbrenner zur erzeugung von heizgasen mit breiter temperaturvarianz
DE3901232A1 (de) * 1988-02-06 1989-08-17 Rolls Royce Plc Brenner fuer ein gasturbinentriebwerk
EP0751345A1 (fr) * 1991-12-24 1997-01-02 Kabushiki Kaisha Toshiba Ensemble à gicleur d'injection de carburant à utiliser dans une chambre de combustion de turbine à gaz
US5444982A (en) * 1994-01-12 1995-08-29 General Electric Company Cyclonic prechamber with a centerbody
WO1995022033A1 (fr) * 1994-02-10 1995-08-17 Solar Turbines Incorporated Injecteur a temperature de buse faible
EP0670456A1 (fr) * 1994-03-04 1995-09-06 NUOVOPIGNONE INDUSTRIE MECCANICHE E FONDERIA S.p.A. Système de combustion perfectionné à pollution réduite pour turbine à gaz
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1070915A1 (fr) * 1999-07-22 2001-01-24 Asea Brown Boveri AG Brûleur à prémélange
EP1070914A1 (fr) * 1999-07-22 2001-01-24 ABB Alstom Power (Schweiz) AG Brûleur à prémélange
US6331109B1 (en) 1999-07-22 2001-12-18 Alstom (Switzerland) Ltd. Premix burner
EP1855054A3 (fr) * 2000-10-05 2008-04-09 ALSTOM Technology Ltd Procéder pour alimenter un brûleur a prémélange an combustible
US7003960B2 (en) 2000-10-05 2006-02-28 Alstom Technology Ltd Method and appliance for supplying fuel to a premixing burner
EP1855054A2 (fr) * 2000-10-05 2007-11-14 ALSTOM Technology Ltd Procéder pour alimenter un brûleur a prémélange an combustible
WO2002029318A1 (fr) * 2000-10-05 2002-04-11 Alstom (Switzerland) Ltd Procede et dispositif pour alimenter un bruleur a melange prealable en combustible
US7871262B2 (en) * 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
WO2009109452A1 (fr) * 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
US8459985B2 (en) 2008-03-07 2013-06-11 Alstom Technology Ltd Method and burner arrangement for the production of hot gas, and use of said method
US8468833B2 (en) 2008-03-07 2013-06-25 Alstom Technology Ltd Burner arrangement, and use of such a burner arrangement
CH703657A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Verfahren zum betrieb einer brenneranordnung sowie brenneranordnung zur durchführung des verfahrens.
EP2423599A3 (fr) * 2010-08-27 2013-07-31 Alstom Technology Ltd Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à l'exécution du procédé

Also Published As

Publication number Publication date
US6019596A (en) 2000-02-01

Similar Documents

Publication Publication Date Title
EP0918190A1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0780629B1 (fr) Brûleur pour un générateur de chaleur
EP0704657B1 (fr) Brûleur
EP0780630B1 (fr) Brûleur pour un générateur de chaleur
EP0918191B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0899508B1 (fr) Brûleur pour un dispositif à chaleur
DE19757189B4 (de) Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
EP0797051B1 (fr) Brûleur pour un générateur de chaleur
EP0694740A2 (fr) Chambre de combustion
EP0718561B1 (fr) Brûleur
EP0994300B1 (fr) Brûleur pour la conduite d'un générateur de chaleur
EP0987493B1 (fr) Brûleur pour générateur de chaleur
EP0931980B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0916894B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0909921B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0851172B1 (fr) Brûleur et méthode pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide et/ou gazeux
EP0751351B1 (fr) Chambre de combustion
EP0903540B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0919768B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE19537636B4 (de) Kraftwerksanlage
EP0913630B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0833104B1 (fr) Brûleur pour le fonctionnement d'une chambre de combustion
DE19914666B4 (de) Brenner für einen Wärmeerzeuger
EP0780628B1 (fr) Brûleur à prémélange pour un générateur de chaleur
EP0899506A2 (fr) Dispositif de combustion

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH DE FR GB IT LI SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 19990920

AKX Designation fees paid

Free format text: AT BE CH DE FR GB IT LI SE

17Q First examination report despatched

Effective date: 20020508

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20020919