EP0909921A1 - 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

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Publication number
EP0909921A1
EP0909921A1 EP97810773A EP97810773A EP0909921A1 EP 0909921 A1 EP0909921 A1 EP 0909921A1 EP 97810773 A EP97810773 A EP 97810773A EP 97810773 A EP97810773 A EP 97810773A EP 0909921 A1 EP0909921 A1 EP 0909921A1
Authority
EP
European Patent Office
Prior art keywords
burner
burner according
flow
downstream
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.)
Granted
Application number
EP97810773A
Other languages
German (de)
English (en)
Other versions
EP0909921B1 (fr
Inventor
Hans Peter 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
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 filed Critical ABB Research Ltd Switzerland
Priority to EP97810773A priority Critical patent/EP0909921B1/fr
Priority to DE59709061T priority patent/DE59709061D1/de
Priority to US09/169,140 priority patent/US5954495A/en
Publication of EP0909921A1 publication Critical patent/EP0909921A1/fr
Application granted granted Critical
Publication of EP0909921B1 publication Critical patent/EP0909921B1/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
    • F23D11/40—Mixing tubes; 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
    • 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
    • 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 simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately 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
    • F23D23/00—Assemblies of two or more burners
    • 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
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air

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 mix quality for everyone Types of fuel is guaranteed.
  • this burner compared to those from the previous state the technology a significant improvement in terms of strengthening flame stability, lower pollutant emissions, lower pulsations, complete Burnout, large operating area, good cross-ignition between the different Burners, compact design, improved mixing, etc., guaranteed, it turns out that this burner has no autonomous arrangements, to drive the gas turbine safely, especially in its transient load ranges to be able to. For example, in the partial load range, the burner must have a support flame get supported. The integration of such precautions in the burner lead to no additional pollutant emissions which the operational and emissions advantages of the underlying burner could question.
  • 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 precautions which strengthen the flame stability for stable operation, especially in the transient load ranges, ensure always under the further task that the Pollutant emissions remain low.
  • the burner is expanded in such a way that in the area of its transition a ring-shaped system for providing to the downstream combustion chamber of a fuel / air mixture is generally provided as Pilot stage acts.
  • Pilot stage acts.
  • Appropriate pilot burners are created in the combustion chamber, which are operated in diffusion mode for stability reasons and directly in the combustion chamber.
  • This air volume initially takes over the cooling of the by means of impingement cooling side facing away from the combustion chamber before it then mixes with the gas and then as a pre-mixed flame with minimized pollutant emissions piloting the main flame in the combustion chamber is maintained.
  • This impingement cooling means that the surface of the pilot gas ring is hot and largely isolated from the flame radiation from the combustion chamber, so that the thermal load in this area is significantly reduced.
  • the object according to the invention also ensures that the minimized Cooling amount can also be fed to the burning process.
  • Fig. 1 shows the overall structure of a burner.
  • a swirl generator 100 is effective, the design of which is shown and described in more detail in the following FIGS. 3-6.
  • This swirl generator 100 is a conical structure which is acted upon tangentially several times by a tangentially flowing combustion air flow 115.
  • the flow formed here is seamlessly transferred to a transition piece 200 using a transition geometry provided downstream of the swirl generator 100, in such a way 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, both parts forming the actual mixing section 220.
  • the mixing section 220 can consist of a single piece, that is to say then that the transition piece 200 and the mixing tube 20 merge into a single coherent structure, the characteristics of each part being retained. If the transition piece 200 and the mixing tube 20 are created from two parts, these are connected by a bushing ring 10, the same bushing ring 10 serving as an anchoring surface for the swirl generator 100 on the head side. Such a bushing ring 10 also has the advantage that different mixing tubes can be used. On the outflow side of the mixing tube 20 is the actual combustion chamber 30 of a combustion chamber, which is here only symbolized by a flame tube.
  • the mixing section 220 largely fulfills the task of providing a defined section downstream of the swirl generator 100, in which a perfect premixing of fuels of different types can be achieved.
  • This mixing section i.e. the mixing pipe 20 in the foreground, furthermore enables loss-free flow guidance, so that no backflow zone or backflow bubble can initially form even in operative connection with the transition geometry, so that the length of the mixing section 220 can influence the quality of the mixture for all types of fuel .
  • this mixing section 220 has yet another property, which consists in that the axial velocity profile itself has a pronounced maximum on the axis, so that the flame cannot be re-ignited from the combustion chamber. However, it is correct that with such a configuration this axial speed drops towards the wall.
  • these bores 21 run at an acute angle with respect to the burner axis 60.
  • the outlet of the transition channels 201 corresponds to the narrowest flow cross-section of the mixing tube 20.
  • the said transition channels 201 therefore bridge the respective cross-sectional difference without adversely affecting the flow formed. If the selected precaution triggers an intolerable pressure loss when guiding the pipe flow 40 along the mixing pipe 20, this can be remedied by providing a diffuser (not shown in the figure) at the end of this mixing pipe.
  • a combustion chamber 30 combustion chamber then adjoins the end of the mixing tube 20, a cross-sectional jump formed by a burner front 70 being present between the two flow cross sections.
  • a pilot burner system 300 is provided concentrically with the mixing tube 20 in the area of its outlet. This consists of an inner annular chamber 301 into which a fuel, preferably a gaseous fuel 303, flows. In addition to this inner annular chamber 301, there is a second annular chamber 302 into which an air quantity 304 flows. Both annular chambers 301, 302 have individually designed through openings, such that the individual media 303, 304 flow into a common downstream annular chamber 308 due to their function.
  • the transfer of the gaseous fuel 303 from the annular chamber 301 into the downstream annular chamber 308 is accomplished by a number of openings 309 arranged in the circumferential direction.
  • the passage geometry of these openings 309 is designed such that the gaseous fuel 303 flows into the downstream annular chamber 308 with a large mixing potential.
  • the other annular chamber 302 closes with a perforated plate 305, the bores 310 provided here being designed in such a way that the air volume 304 flowing through there impacts cooling on the base plate 307 of the downstream annular chamber 308.
  • This base plate has the function of a heat protection plate against the calorific load from the combustion chamber 30, so that this impingement cooling must be extremely efficient here.
  • this air mixes within this annular chamber 308 with the inflowing gaseous fuel 303 from the openings 309 of the upstream annular chamber 301 before this mixture through a number of bores 306 arranged on the combustion chamber side into the combustion chamber 30 flows out.
  • the mixture flowing out burns as a premixed diffusion flame with minimized pollutant emissions and forms accordingly Bore 306 a pilot burner acting in the combustion chamber 30, which one guaranteed stable operation.
  • 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 carries out the flushing of the fuel lance there.
  • These holes 161 are slanted forward so that it is appropriate axial component arises on the burner axis 60.
  • the first part of the burner according to FIG. 1 forms the swirl generator 100 shown in FIG. 3. It consists of two hollow, conical partial bodies 101, 102, which are nested one inside the other.
  • the number of conical partial bodies can of course be greater than two, as shown in FIGS. 5 and 6; This depends on the operating mode of the entire burner, as will be explained in more detail below. In certain operating constellations, it is not excluded to provide a swirl generator consisting of a single spiral.
  • the offset of the respective central axis or longitudinal symmetry axes 101b, 102b (see FIG. 4) of the conical partial bodies 101, 102 to one another creates a tangential channel, ie an air inlet slot 119, 120 (see FIG.
  • the conical shape of the partial bodies 101, 102 shown in the flow direction has a specific fixed angle.
  • the partial bodies 101, 102 can have an increasing or decreasing cone inclination in the direction of flow, similar to a trumpet or. Tulip.
  • the last two forms are not included in the drawing, since they can be easily understood by a person skilled in the art.
  • the two conical partial bodies 101, 102 each have a cylindrical, ring-shaped initial part 101a.
  • the fuel nozzle 103 already mentioned under FIG. 2 is accommodated in the region of this cylindrical starting part and is preferably operated with a liquid fuel 112.
  • the injection 104 of this fuel 112 coincides approximately with the narrowest cross section of the conical cavity 114 formed by the conical partial bodies 101, 102.
  • the injection capacity and the type of this fuel nozzle 103 depend on the specified parameters of the respective burner.
  • the tapered partial bodies 101, 102 further 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 a gaseous fuel 113 is preferably injected into the combustion air 115 flowing through there, such as arrows 116 symbolize this.
  • These fuel lines 108, 109 are preferably arranged at the latest at the end of the tangential inflow, before entering the cone cavity 114, in order to obtain an optimal air / fuel mixture.
  • the fuel 112 brought up through the fuel nozzle 103 is normally a liquid fuel, and it is readily possible to form a mixture with another medium, for example with a recirculated flue gas.
  • This fuel 112 is injected into the cone cavity 114 at a preferably very acute angle.
  • a conical fuel spray 105 thus forms from the fuel nozzle 103 and is enclosed and broken down by the rotating combustion air 115 flowing in tangentially.
  • the concentration of the injected fuel 112 is then continuously reduced in the axial direction by the inflowing combustion air 115 to mix in the direction of evaporation. If a gaseous fuel 113 is introduced via the opening nozzles 117, the fuel / air mixture is formed directly at the end of the air inlet slots 119, 120.
  • combustion air 115 is additionally preheated or, for example, enriched with a recirculated flue gas or exhaust gas, this provides lasting support the evaporation of the liquid fuel 112 before this mixture flows into the downstream stage, here in the transition piece 200 (see FIGS. 1 and 7).
  • liquid fuels should be supplied via lines 108, 109.
  • a reduction in the size of the tangential air inlet slots 119, 120 already favors the faster formation of a backflow zone in the region of the swirl generator.
  • the axial speed within the swirl generator 100 can be increased or stabilized by a corresponding supply of an air quantity described in more detail in FIG. 2 (item 160).
  • a corresponding swirl generation in operative connection with the downstream transition piece 200 prevents the formation of flow separations within the mixing tube downstream of the swirl generator 100.
  • the design of the swirl generator 100 is furthermore particularly suitable for changing the size of the tangential air inlet slots 119, 120, with which a relatively large operational bandwidth can be recorded without changing the overall length of the swirl generator 100.
  • the partial bodies 101, 102 can also be displaced relative to one another in another plane, as a result of which an overlap thereof can even be provided. It is also possible to interleave the partial bodies 101, 102 in a spiral manner by counter-rotating movement. It is thus possible to vary the shape, the size and the configuration of the tangential air inlet slots 119, 120 as desired, with which the swirl generator 100 can be used universally without changing its overall length.
  • 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 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 °.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP97810773A 1997-10-14 1997-10-14 Brûleur pour la mise en oeuvre d'un générateur de chaleur Expired - Lifetime EP0909921B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP97810773A EP0909921B1 (fr) 1997-10-14 1997-10-14 Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE59709061T DE59709061D1 (de) 1997-10-14 1997-10-14 Brenner für den Betrieb eines Wärmeerzeugers
US09/169,140 US5954495A (en) 1997-10-14 1998-10-09 Burner for operating a heat generator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810773A EP0909921B1 (fr) 1997-10-14 1997-10-14 Brûleur pour la mise en oeuvre d'un générateur de chaleur

Publications (2)

Publication Number Publication Date
EP0909921A1 true EP0909921A1 (fr) 1999-04-21
EP0909921B1 EP0909921B1 (fr) 2003-01-02

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EP97810773A Expired - Lifetime EP0909921B1 (fr) 1997-10-14 1997-10-14 Brûleur pour la mise en oeuvre d'un générateur de chaleur

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US (1) US5954495A (fr)
EP (1) EP0909921B1 (fr)
DE (1) DE59709061D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1213536A3 (fr) * 2000-12-11 2002-10-23 ALSTOM Power N.V. Brûleur à prémélange avec brûleur pilote catalytique
DE102008000050A1 (de) * 2007-08-07 2009-02-12 Alstom Technology Ltd. Brenner für eine Brennkammer einer Turbogruppe

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE237101T1 (de) * 1998-01-23 2003-04-15 Alstom Switzerland Ltd Brenner für den betrieb eines wärmeerzeugers
EP0987493B1 (fr) * 1998-09-16 2003-08-06 Abb Research Ltd. Brûleur pour générateur de chaleur
DE59810284D1 (de) * 1998-10-14 2004-01-08 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
US20030229559A1 (en) * 2002-04-09 2003-12-11 Panttaja James T. Asset management platform
EP1389713A1 (fr) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
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
US7303388B2 (en) * 2004-07-01 2007-12-04 Air Products And Chemicals, Inc. Staged combustion system with ignition-assisted fuel lances
CN101243287B (zh) * 2004-12-23 2013-03-27 阿尔斯托姆科技有限公司 具有混合段的预混燃烧器
EP2110601A1 (fr) * 2008-04-15 2009-10-21 Siemens Aktiengesellschaft Brûleur
EP2650612A1 (fr) * 2012-04-10 2013-10-16 Siemens Aktiengesellschaft Brûleur
US9400104B2 (en) 2012-09-28 2016-07-26 United Technologies Corporation Flow modifier for combustor fuel nozzle tip

Citations (8)

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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
EP0376259A2 (fr) * 1988-12-26 1990-07-04 Hitachi, Ltd. Chaudière à basse émission de NOx
JPH0682084A (ja) * 1992-09-02 1994-03-22 Daikin Ind Ltd 空気調和装置の運転制御装置
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
JPH0882419A (ja) * 1994-09-14 1996-03-26 Hitachi Ltd ガスタービン用燃焼器
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur
EP0780630A2 (fr) * 1995-12-21 1997-06-25 Abb Research Ltd. Brûleur pour un générateur de chaleur
EP0797051A2 (fr) * 1996-03-20 1997-09-24 Abb Research Ltd. Brûleur pour un générateur de chaleur

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4411623A1 (de) * 1994-04-02 1995-10-05 Abb Management Ag Vormischbrenner
DE4416650A1 (de) * 1994-05-11 1995-11-16 Abb Management Ag Verbrennungsverfahren für atmosphärische Feuerungsanlagen

Patent Citations (8)

* 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
EP0376259A2 (fr) * 1988-12-26 1990-07-04 Hitachi, Ltd. Chaudière à basse émission de NOx
JPH0682084A (ja) * 1992-09-02 1994-03-22 Daikin Ind Ltd 空気調和装置の運転制御装置
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
JPH0882419A (ja) * 1994-09-14 1996-03-26 Hitachi Ltd ガスタービン用燃焼器
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur
EP0780630A2 (fr) * 1995-12-21 1997-06-25 Abb Research Ltd. Brûleur pour un générateur de chaleur
EP0797051A2 (fr) * 1996-03-20 1997-09-24 Abb Research Ltd. Brûleur pour un générateur de chaleur

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Title
PATENT ABSTRACTS OF JAPAN vol. 18, no. 341 (M - 1629) 28 June 1994 (1994-06-28) *
PATENT ABSTRACTS OF JAPAN vol. 96, no. 7 31 July 1996 (1996-07-31) *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1213536A3 (fr) * 2000-12-11 2002-10-23 ALSTOM Power N.V. Brûleur à prémélange avec brûleur pilote catalytique
US6679061B2 (en) 2000-12-11 2004-01-20 Alstom Technology Ltd. Premix burner arrangement for operating a combustion chamber
DE102008000050A1 (de) * 2007-08-07 2009-02-12 Alstom Technology Ltd. Brenner für eine Brennkammer einer Turbogruppe

Also Published As

Publication number Publication date
EP0909921B1 (fr) 2003-01-02
DE59709061D1 (de) 2003-02-06
US5954495A (en) 1999-09-21

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