EP0780629A2 - Brûleur pour un générateur de chaleur - Google Patents

Brûleur pour un générateur de chaleur Download PDF

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Publication number
EP0780629A2
EP0780629A2 EP96810804A EP96810804A EP0780629A2 EP 0780629 A2 EP0780629 A2 EP 0780629A2 EP 96810804 A EP96810804 A EP 96810804A EP 96810804 A EP96810804 A EP 96810804A EP 0780629 A2 EP0780629 A2 EP 0780629A2
Authority
EP
European Patent Office
Prior art keywords
flow
burner according
swirl generator
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.)
Granted
Application number
EP96810804A
Other languages
German (de)
English (en)
Other versions
EP0780629B1 (fr
EP0780629A3 (fr
Inventor
Hans Peter Knöpfel
Thomas Ruch
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 RESEARCH Ltd
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
Publication of EP0780629A2 publication Critical patent/EP0780629A2/fr
Publication of EP0780629A3 publication Critical patent/EP0780629A3/fr
Application granted granted Critical
Publication of EP0780629B1 publication Critical patent/EP0780629B1/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 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details
    • 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 
    • 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 according to the preamble of claim 1.
  • a cone-shaped burner known as a double-cone burner, consisting of several shells, is known for generating a closed swirl flow in the cone head, which becomes unstable due to the increasing swirl along the cone tip and changes into an annular swirl flow with backflow in the core.
  • Fuels such as gaseous fuels, are injected along the channels formed by the individual adjacent shells, also called air inlet slots, and mixed homogeneously with the air before the combustion starts by ignition at the stagnation point of the backflow zone or backflow bubble, which is used as a flame holder.
  • Liquid fuels are preferably injected via a central nozzle on the burner head and then evaporate in the cone cavity.
  • the invention seeks to remedy this.
  • the invention is based on the object of proposing, in a burner of the type mentioned, precautions by which a perfect premixing of fuels of different types is achieved and by which an operationally reliable and optimal flame positioning is achieved.
  • the proposed burner has a swirl generator on the head side and upstream of a mixing section, which can preferably be designed such that the basic aerodynamic principles of the so-called double-cone burner according to EP-A1-0 321 809 are used. In principle, however, the use of an axial or radial swirl generator is also possible.
  • the mixing section itself preferably consists of a tubular mixing element, hereinafter referred to as the mixing tube, which permits perfect premixing of fuels of various types.
  • the flow from the swirl generator is introduced seamlessly into the mixing tube: this is done by means of a transition geometry which consists of transition channels which are excluded in the initial phase of this mixing tube, and which transfer the flow into the subsequent effective flow cross-section of the mixing tube.
  • This low-loss flow introduction between the swirl generator and the mixing tube initially prevents the immediate formation of a backflow zone at the outlet of the swirl generator.
  • the swirl strength in the swirl generator is selected via its geometry so that the swirl does not burst in the mixing tube, but further downstream at the combustion chamber inlet, the length of this mixing tube being dimensioned such that there is sufficient mixing quality for all types of fuel. If, for example, the swirl generator used is constructed according to the basic principles of the double-cone burner, the swirl strength results from the design of the corresponding cone angle, the air inlet slots and their number.
  • the axial speed profile has a pronounced maximum on the axis and thus prevents reignitions in this area.
  • the axial speed drops towards the wall.
  • various precautions are provided: For example, the entire speed level can be raised by using a mixing tube with a sufficiently small diameter.
  • Another possibility is to only increase the speed in the outer region of the mixing tube, in that a small part of the combustion air flows into the mixing tube via an annular gap or through filming holes downstream of the transition channels.
  • transition channels mentioned for introducing the flow from the swirl generator into the mixing tube it can be said that the course of these transition channels can be designed to narrow or widen in a spiral fashion, in accordance with the effective subsequent flow cross-section of the mixing tube.
  • Part of the pressure loss that may be generated can be compensated for by attaching a diffuser to the end of the mixing tube.
  • a venturi section can also be provided in this area or upstream.
  • the combustion chamber connects with a cross-sectional jump.
  • a central backflow zone is formed here, the properties of which are those of a flame holder.
  • the generation of a stable backflow zone requires a sufficiently high number of swirls in the mixing tube. However, if this is initially undesirable, stable return flow zones can be created at the end of the pipe by supplying small, strongly swirled air volumes, 5-20% of the total air volume.
  • 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. 2-5.
  • 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 tube 20, both parts forming the actual mixing tube 220, also called the mixing section, of the burner.
  • the mixing tube 220 can consist of a single piece, that is to say then that the transition piece 200 and tube 20 are fused into a single coherent structure, the characteristics of each part being retained. If the transition piece 200 and the tube 20 are created from two parts, they 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.
  • the actual combustion chamber 30 is located on the outflow side of the tube 20 and is here only symbolized by the flame tube.
  • the mixing tube 220 fulfills the condition that a defined mixing section is provided downstream of the swirl generator 100, in which a perfect premixing of fuels of different types is achieved.
  • This mixing section that is to say the mixing tube 220, furthermore enables loss-free flow guidance, so that it is also in operative connection cannot initially form a backflow zone with the transition geometry, which means that the length of the mixing tube 220 can influence the quality of the mixture for all types of fuel.
  • this mixing tube 220 has yet another property, which consists in the fact that in the mixing tube 220 itself the axial speed profile 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.
  • the mixing tube 220 is provided with a number of regularly or irregularly distributed bores 21 of various cross-sections and directions in the flow and circumferential direction, through which an amount of air flows into the interior of the mixing tube 220 and along the wall in the Inducing an increase in speed in the sense of filming.
  • Another possibility of achieving the same effect is that the flow cross section of the mixing tube 220 is narrowed on the downstream side of the transition channels 201, which form the transition geometry already mentioned, as a result of which the overall speed level within the mixing tube 220 is increased.
  • 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 220.
  • the transition channels 201 mentioned 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 220, this can be remedied by providing a diffuser (not shown in the figure) at the end of the mixing pipe.
  • a combustion chamber 30 adjoins the end of the mixing tube 220, a cross-sectional jump occurring between the two flow cross sections. Only here does one form central backflow zone 50, which has the properties of a flame holder.
  • a flow-like edge zone forms in this cross-sectional jump during operation, in which vortex detachments arise due to the prevailing negative pressure, this leads to an increased ring stabilization of the backflow zone 50.
  • the combustion chamber 30 has a number of openings 31 through which an air quantity flows directly into the cross-sectional jump flows, and there contributes the others below that the ring stabilization of the backflow zone 50 is strengthened.
  • the generation of a stable backflow zone 50 also requires a sufficiently high number of twists in a pipe. If this is initially undesirable, stable backflow zones can be created by supplying small, strongly swirled air flows at the pipe end, for example through tangential openings. It is assumed here that the amount of air required for this is about 5-20% of the total amount of air.
  • FIG. 3 is used at the same time as FIG. 2. Furthermore, in order not to make this FIG. 2 unnecessarily confusing, the guide plates 121a, 121b shown schematically according to FIG. 3 have only been hinted at in it. In the description of FIG. 2, reference is made below to the figures mentioned as required.
  • the first part of the burner according to FIG. 1 forms the swirl generator 100 shown in FIG. 2. 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. 4 and 5; this depends on how each further will be explained in more detail below, depending on the mode of operation of the entire burner. 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 201b, 202b of the conical partial bodies 101, 102 to one another creates a tangential channel, that is to say an air inlet slot 119, 120 (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 tapered partial bodies 101, 102 each have a cylindrical starting part 101a, 102a, which, similarly to the conical partial bodies 101, 102, also run offset from one another, so that the tangential air inlet slots 119, 120 are present over the entire length of the swirl generator 100.
  • a nozzle 103 is preferably accommodated for a liquid fuel 112, the injection 104 of which 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 nozzle 103 depend on the given parameters of the respective burner.
  • the swirl generator 100 can be designed in a purely conical manner, that is to say without cylindrical starting parts 101a, 102a.
  • the conical sub-bodies 101, 102 each further 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 is preferably provided 113 is injected into the combustion air 115 flowing through there, as is to be symbolized by the arrows 116.
  • These fuel lines 108, 109 are preferably placed 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 in through the nozzle 103 is normally a liquid fuel, and it is readily possible to form a mixture with another medium. This fuel 112 is injected into the cone cavity 114 at an acute angle.
  • a cone-shaped fuel spray 105 is thus formed from the nozzle 103 and is enclosed by the rotating combustion air 115 flowing in tangentially.
  • the concentration of the injected fuel 112 is continuously reduced by the inflowing combustion air 115 to mix in the direction of evaporation.
  • 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.
  • the combustion air 115 is additionally preheated or, for example, enriched with a recirculated flue gas or exhaust gas, this provides lasting support the vaporization of the liquid fuel 112 before this mixture flows into the downstream stage.
  • the design of the swirl generator 100 is furthermore excellently 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, size and 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.
  • FIG. 3 now shows the geometric configuration of the guide plates 121a, 121b. They have a flow introduction function, which, depending on their length, extend the respective end of the tapered partial bodies 101, 102 in the direction of flow relative to the combustion air 115.
  • the channeling of the combustion air 115 into the cone cavity 114 can be optimized by opening or closing the guide plates 121a, 121b about a pivot point 123 located in the region of the entry of this channel into the cone cavity 114, in particular this is necessary if the original gap size of the tangential air inlet slots 119, 120 should be changed dynamically.
  • these dynamic arrangements can also be provided statically, in that guide baffles as required form a fixed component with the tapered partial bodies 101, 102.
  • the swirl generator 100 can also be operated without baffles, or other aids can be provided for this.
  • the swirl generator 100 is now composed of four partial bodies 130, 131, 132, 133.
  • the associated longitudinal symmetry axes for each partial body are marked with the letter a.
  • this configuration it should be said that, due to the lower swirl strength generated in this way and in cooperation with a correspondingly enlarged slot width, it is ideally suited to prevent the vortex flow from bursting in the mixing tube on the downstream side of the swirl generator, so that the mixing tube can best fulfill the role intended for it .
  • FIG. 5 differs from FIG. 4 in that the partial bodies 140, 141, 142, 143 have a blade profile shape which is provided to provide a certain flow. Otherwise the mode of operation of the swirl generator has remained the same.
  • the admixture of the fuel 116 in the combustion air flow 115 takes place from the inside of the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades.
  • the longitudinal axes of symmetry to the individual partial bodies are identified by the letter a.
  • the transition geometry is constructed for a swirl generator 100 with four partial bodies, corresponding to FIG. 4 or 5. Accordingly, the transition geometry as a natural extension of the upstream partial body four transition channels 201, whereby the conical quarter surface of the partial body is extended until it the wall of the tube 20 or. of the mixing tube 220 cuts.
  • the same considerations also apply if the swirl generator is constructed from a principle other than that described under FIG. 2.
  • the surface of the individual transition channels 201 which runs downward in the direction of flow has a shape which runs in a spiral in the direction of flow and which describes a crescent shape, corresponding to FIG The fact that in the present case the flow cross section of the transition piece 200 widens conically in the flow direction.
  • the swirl angle of the transition channels 201 in the flow direction is selected such that the pipe flow then still has a sufficiently large distance up to the cross-sectional jump at the combustion chamber inlet in order to achieve a perfect premixing with the injected fuel. Furthermore, the above-mentioned measures also increase the axial speed 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 in the axial speed profile towards the center of the mixing tube, so that the risk of early ignition is decisively counteracted.
  • Fig. 7 shows the tear-off edge already mentioned, which is formed at the burner outlet.
  • the flow cross-section of the tube 20 receives a transition radius R in this area, the size of which basically depends on the flow within the tube 20.
  • This radius R is selected so that the flow is applied to the wall and the swirl number can increase sharply.
  • the size of the radius R can be quantitatively defined so that it is> 10% of the inner diameter d of the tube 20.
  • the backflow bladder 50 now increases enormously.
  • This radius R extends to the exit plane of the tube 20, the angle ⁇ between the beginning and end of the curvature being ⁇ 90 °.
  • the tear-off edge A runs along one leg of the angle ⁇ into the interior of the tube 20 and thus forms a tear-off step S with respect to the front point of the tear-off edge A, the depth of which is> 3 mm.
  • the edge running parallel to the exit plane of the tube 20 can be brought back to the exit plane level using a curved course.
  • the angle ⁇ ' which extends between the tangent of the tear-off edge A and perpendicular to the exit plane of the tube 20, is the same size as the angle ⁇ .

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  • 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)
  • Gas Burners (AREA)
  • Sorption Type Refrigeration Machines (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
EP96810804A 1995-12-21 1996-11-18 Brûleur pour un générateur de chaleur Expired - Lifetime EP0780629B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19547913A DE19547913A1 (de) 1995-12-21 1995-12-21 Brenner für einen Wärmeerzeuger
DE19547913 1995-12-21

Publications (3)

Publication Number Publication Date
EP0780629A2 true EP0780629A2 (fr) 1997-06-25
EP0780629A3 EP0780629A3 (fr) 1998-08-19
EP0780629B1 EP0780629B1 (fr) 2001-07-11

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EP96810804A Expired - Lifetime EP0780629B1 (fr) 1995-12-21 1996-11-18 Brûleur pour un générateur de chaleur

Country Status (7)

Country Link
US (1) US5735687A (fr)
EP (1) EP0780629B1 (fr)
JP (1) JPH09184606A (fr)
KR (1) KR970046984A (fr)
AT (1) ATE203101T1 (fr)
CA (1) CA2190805A1 (fr)
DE (2) DE19547913A1 (fr)

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EP0903540A1 (fr) 1997-09-19 1999-03-24 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0909921A1 (fr) 1997-10-14 1999-04-21 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0913630A1 (fr) 1997-10-31 1999-05-06 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0916894A1 (fr) 1997-11-13 1999-05-19 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0918190A1 (fr) 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0918191A1 (fr) 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0919768A1 (fr) 1997-11-25 1999-06-02 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0899506A3 (fr) * 1997-08-30 1999-06-16 Abb Research Ltd. Dispositif de combustion
DE19757189A1 (de) * 1997-12-22 1999-06-24 Abb Research Ltd Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
EP0931980A1 (fr) 1998-01-23 1999-07-28 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0994300A1 (fr) 1998-10-14 2000-04-19 Abb Research Ltd. Brûleur pour la conduite d'un générateur de chaleur
EP1065346A1 (fr) 1999-07-02 2001-01-03 Asea Brown Boveri AG Chambre de combustion pour une turbine à gaz
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
EP1182398A1 (fr) 2000-08-21 2002-02-27 Alstom (Switzerland) Ltd Procédé pour accroítre la stabilité fluidique d'un brûleur de prémélange ainsi que brûleur de prémélange pour mettre en oeuvre le procédé
EP1199516A1 (fr) * 2000-10-11 2002-04-24 ALSTOM (Switzerland) Ltd Brûleur
EP1217297A1 (fr) * 2000-12-22 2002-06-26 ALSTOM Power N.V. Brûleur à stabilité de flamme élévée
EP1262714A1 (fr) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
EP1279898A2 (fr) 2001-07-26 2003-01-29 ALSTOM (Switzerland) Ltd Brûleur à prémélange offrant une haute stabilité de flamme
US6558154B2 (en) 2000-11-13 2003-05-06 Alstom (Switzerland) Ltd Burner system with staged fuel injection and method for its operation
US6679060B2 (en) 2000-12-16 2004-01-20 Alstom Technology Ltd Method for operating a premix burner
EP1389713A1 (fr) 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
US6969251B2 (en) 2002-10-12 2005-11-29 Alstom Technology Ltd Burner
US7003957B2 (en) 2001-10-19 2006-02-28 Alstom Technology Ltd Burner for synthesis gas
US7013648B2 (en) 2002-05-16 2006-03-21 Alstom Technology Ltd. Premix burner
US7189073B2 (en) 2000-10-16 2007-03-13 Alstom Technology Ltd. Burner with staged fuel injection
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
EP2058590A1 (fr) 2007-11-09 2009-05-13 ALSTOM Technology Ltd Procédé de fonctionnement d'un brûleur
WO2009068424A1 (fr) 2007-11-27 2009-06-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
US7610761B2 (en) 2005-03-23 2009-11-03 Alstom Technology Ltd. Method and device for the combustion of hydrogen in a premix burner
US7871262B2 (en) 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
WO2011032935A2 (fr) 2009-09-17 2011-03-24 Alstom Technology Ltd. Procédé pour brûler des combustibles gazeux, riches en hydrogène, dans un brûleur ainsi que brûleur pour la mise en oeuvre du procédé
US7972133B2 (en) 2006-03-27 2011-07-05 Alstom Technology Ltd. Burner for the operation of a heat generator and method of use
EP2703721A1 (fr) 2012-08-31 2014-03-05 Alstom Technology Ltd Brûleur à prémélange
EP3228937A1 (fr) 2016-04-08 2017-10-11 Ansaldo Energia Switzerland AG Procédé de combustion d'un combustible et dispositif de combustion
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US9890955B2 (en) 2012-08-24 2018-02-13 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas mixer
EP3306194A1 (fr) 2016-10-06 2018-04-11 Ansaldo Energia IP UK Limited Élément de paroi de chambre de combustion et son procédé de fabrication
US10151487B2 (en) 2014-01-10 2018-12-11 Ansaldo Energia Switzerland AG Sequential combustion arrangement with dilution gas
US10422535B2 (en) 2013-04-26 2019-09-24 Ansaldo Energia Switzerland AG Can combustor for a can-annular combustor arrangement in a gas turbine
EP2179222B2 (fr) † 2007-08-07 2021-12-01 Ansaldo Energia IP UK Limited Brûleur pour une chambre de combustion d'un turbogroupe

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US5954496A (en) * 1996-09-25 1999-09-21 Abb Research Ltd. Burner for operating a combustion chamber
DE19736902A1 (de) * 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE59710093D1 (de) 1997-10-08 2003-06-18 Alstom Switzerland Ltd Verfahren zur Verbrennung von gasförmigen, flüssigen sowie mittel-oder niederkalorischen Brennstoffen in einem Brenner
EP0987493B1 (fr) 1998-09-16 2003-08-06 Abb Research Ltd. Brûleur pour générateur de chaleur
DE19859829A1 (de) 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
DE19914666B4 (de) 1999-03-31 2009-08-20 Alstom Brenner für einen Wärmeerzeuger
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DE10121768B4 (de) * 2001-05-04 2007-03-01 Robert Bosch Gmbh Durchmischungsvorrichtung für Gase in Brennstoffzellen
DE10210034B4 (de) * 2002-03-07 2009-10-01 Webasto Ag Mobiles Heizgerät mit einer Brennstoffversorgung
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EP1601913A1 (fr) 2003-03-07 2005-12-07 Alstom Technology Ltd Bruleur de premelange
WO2006069906A1 (fr) 2004-12-23 2006-07-06 Alstom Technology Ltd Procede de fonctionnement d'un ensemble turbine a gaz
JP5453322B2 (ja) * 2008-03-07 2014-03-26 アルストム テクノロジー リミテッド バーナ装置並びにバーナ装置の使用
US8561602B2 (en) * 2008-12-24 2013-10-22 Agio International Company, Ltd. Gas feature and method
US8256226B2 (en) * 2009-04-23 2012-09-04 General Electric Company Radial lean direct injection burner
RU2561956C2 (ru) * 2012-07-09 2015-09-10 Альстом Текнолоджи Лтд Газотурбинная система сгорания
EP2685161B1 (fr) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Agencement de chambre de combustion, en particulier pour turbine à gaz
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EP2857658A1 (fr) 2013-10-01 2015-04-08 Alstom Technology Ltd Turbine à gaz avec agencement de combustion séquentielle
EP2921779B1 (fr) 2014-03-18 2017-12-06 Ansaldo Energia Switzerland AG Chambre de combustion avec manchon de refroidissement
JP6602004B2 (ja) * 2014-09-29 2019-11-06 川崎重工業株式会社 燃料噴射器及びガスタービン
EP3015771B1 (fr) 2014-10-31 2020-01-01 Ansaldo Energia Switzerland AG Agencement de chambre de combustion pour une turbine à gaz
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EP3130848B1 (fr) 2015-08-12 2019-01-16 Ansaldo Energia Switzerland AG Dispositif à combustion séquentielle avec gaz de refroidissement pour la dilution
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EP0903540A1 (fr) 1997-09-19 1999-03-24 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0909921A1 (fr) 1997-10-14 1999-04-21 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
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EP0913630A1 (fr) 1997-10-31 1999-05-06 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6059565A (en) * 1997-10-31 2000-05-09 Abb Alstom Power (Switzereland) Ltd Burner for operating a heat generator
EP0916894A1 (fr) 1997-11-13 1999-05-19 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6027331A (en) * 1997-11-13 2000-02-22 Abb Research Ltd. Burner for operating a heat generator
EP0918191A1 (fr) 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
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EP0918190A1 (fr) 1997-11-21 1999-05-26 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6155820A (en) * 1997-11-21 2000-12-05 Abb Research Ltd. Burner for operating a heat generator
US5954490A (en) * 1997-11-25 1999-09-21 Abb Research Ltd. Burner for operating a heat generator
EP0919768A1 (fr) 1997-11-25 1999-06-02 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE19757189A1 (de) * 1997-12-22 1999-06-24 Abb Research Ltd Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
US6045351A (en) * 1997-12-22 2000-04-04 Abb Alstom Power (Switzerland) Ltd Method of operating a burner of a heat generator
DE19757189B4 (de) * 1997-12-22 2008-05-08 Alstom Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
EP0931980A1 (fr) 1998-01-23 1999-07-28 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US6186775B1 (en) 1998-01-23 2001-02-13 Abb Research Ltd. Burner for operating a heat generator
EP0994300A1 (fr) 1998-10-14 2000-04-19 Abb Research Ltd. Brûleur pour la conduite d'un générateur de chaleur
US6152726A (en) * 1998-10-14 2000-11-28 Asea Brown Boveri Ag Burner for operating a heat generator
EP1065346A1 (fr) 1999-07-02 2001-01-03 Asea Brown Boveri AG Chambre de combustion pour une turbine à gaz
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
EP1182398A1 (fr) 2000-08-21 2002-02-27 Alstom (Switzerland) Ltd Procédé pour accroítre la stabilité fluidique d'un brûleur de prémélange ainsi que brûleur de prémélange pour mettre en oeuvre le procédé
EP1199516A1 (fr) * 2000-10-11 2002-04-24 ALSTOM (Switzerland) Ltd Brûleur
US6901760B2 (en) 2000-10-11 2005-06-07 Alstom Technology Ltd Process for operation of a burner with controlled axial central air mass flow
US7189073B2 (en) 2000-10-16 2007-03-13 Alstom Technology Ltd. Burner with staged fuel injection
US6558154B2 (en) 2000-11-13 2003-05-06 Alstom (Switzerland) Ltd Burner system with staged fuel injection and method for its operation
US6817188B2 (en) 2000-12-16 2004-11-16 Alstom (Switzerland) Ltd Method for operating a premix burner
US6679060B2 (en) 2000-12-16 2004-01-20 Alstom Technology Ltd Method for operating a premix burner
US6640545B2 (en) 2000-12-22 2003-11-04 Alstom Ltd. Burner with high flame stability
EP1217297A1 (fr) * 2000-12-22 2002-06-26 ALSTOM Power N.V. Brûleur à stabilité de flamme élévée
US6672863B2 (en) 2001-06-01 2004-01-06 Alstom Technology Ltd Burner with exhaust gas recirculation
EP1262714A1 (fr) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
EP1279898A3 (fr) * 2001-07-26 2003-04-16 ALSTOM (Switzerland) Ltd Brûleur à prémélange offrant une haute stabilité de flamme
US6834504B2 (en) 2001-07-26 2004-12-28 Alstom Technology Ltd Premix burner with high flame stability having a net-like structure within the mixing section
EP1279898A2 (fr) 2001-07-26 2003-01-29 ALSTOM (Switzerland) Ltd Brûleur à prémélange offrant une haute stabilité de flamme
US7003957B2 (en) 2001-10-19 2006-02-28 Alstom Technology Ltd Burner for synthesis gas
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
US7013648B2 (en) 2002-05-16 2006-03-21 Alstom Technology Ltd. Premix burner
EP1389713A1 (fr) 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
US7140183B2 (en) 2002-08-12 2006-11-28 Alstom Technology Ltd. Premixed exit ring pilot burner
US6969251B2 (en) 2002-10-12 2005-11-29 Alstom Technology Ltd Burner
US7871262B2 (en) 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
US7610761B2 (en) 2005-03-23 2009-11-03 Alstom Technology Ltd. Method and device for the combustion of hydrogen in a premix burner
US7972133B2 (en) 2006-03-27 2011-07-05 Alstom Technology Ltd. Burner for the operation of a heat generator and method of use
EP2179222B2 (fr) † 2007-08-07 2021-12-01 Ansaldo Energia IP UK Limited Brûleur pour une chambre de combustion d'un turbogroupe
EP2058590A1 (fr) 2007-11-09 2009-05-13 ALSTOM Technology Ltd Procédé de fonctionnement d'un brûleur
US9103547B2 (en) 2007-11-09 2015-08-11 Alstom Technology Ltd Method for operating a burner
WO2009068424A1 (fr) 2007-11-27 2009-06-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
US8066509B2 (en) 2007-11-27 2011-11-29 Alstom Technology Ltd. Method and device for combusting hydrogen in a premix burner
WO2011032935A2 (fr) 2009-09-17 2011-03-24 Alstom Technology Ltd. Procédé pour brûler des combustibles gazeux, riches en hydrogène, dans un brûleur ainsi que brûleur pour la mise en oeuvre du procédé
US8549860B2 (en) 2009-09-17 2013-10-08 Alstom Technology Ltd Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method
DE112010003677B4 (de) 2009-09-17 2023-10-26 Ansaldo Energia Switzerland AG Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens
US9890955B2 (en) 2012-08-24 2018-02-13 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas mixer
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EP2703721A1 (fr) 2012-08-31 2014-03-05 Alstom Technology Ltd Brûleur à prémélange
US9400105B2 (en) 2012-08-31 2016-07-26 General Electric Technology Gmbh Premix burner
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Also Published As

Publication number Publication date
DE59607269D1 (de) 2001-08-16
JPH09184606A (ja) 1997-07-15
CA2190805A1 (fr) 1997-06-22
ATE203101T1 (de) 2001-07-15
EP0780629B1 (fr) 2001-07-11
DE19547913A1 (de) 1997-06-26
EP0780629A3 (fr) 1998-08-19
US5735687A (en) 1998-04-07
KR970046984A (ko) 1997-07-26

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