EP0704657A2 - Brûleur - Google Patents

Brûleur Download PDF

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Publication number
EP0704657A2
EP0704657A2 EP95810587A EP95810587A EP0704657A2 EP 0704657 A2 EP0704657 A2 EP 0704657A2 EP 95810587 A EP95810587 A EP 95810587A EP 95810587 A EP95810587 A EP 95810587A EP 0704657 A2 EP0704657 A2 EP 0704657A2
Authority
EP
European Patent Office
Prior art keywords
flow
burner according
section
swirl generator
mixing 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
EP95810587A
Other languages
German (de)
English (en)
Other versions
EP0704657A3 (fr
EP0704657B1 (fr
Inventor
Thomas Ruck
Thomas Dr. Sattelmayer
Christian Dr. Steinbach
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 Management AG
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 Management AG filed Critical ABB Management AG
Publication of EP0704657A2 publication Critical patent/EP0704657A2/fr
Publication of EP0704657A3 publication Critical patent/EP0704657A3/fr
Application granted granted Critical
Publication of EP0704657B1 publication Critical patent/EP0704657B1/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
    • 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 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/40—Inducing local whirls around flame
    • 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
    • F23D2202/00—Liquid fuel 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
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability

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 as characterized in the claims, is based on the object of proposing precautions for a burner of the type mentioned at the outset by which a perfect premixing of fuels of different types 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 seamlessly introduced into the mixing tube: this is done by means of a transition geometry that consists of transition channels that are excluded in the initial phase of this mixing tube and that convert the flow into the subsequent effective flow cross-section of the mixing tube.
  • This lossless Initiation of flow 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.
  • Part of the pressure loss that may be generated can be compensated for by attaching a diffuser to the end of the mixing tube.
  • 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.
  • 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 turns out to be spiraling narrowing or widening, in accordance with the effective subsequent flow cross-section of the mixing tube.
  • 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 confiquration 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 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 are used can be.
  • 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 i.e. the mixing tube 220, furthermore enables loss-free flow guidance, so that no backflow zone can initially form even in operative connection with the transition geometry, so 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 one along the wall Increase in speed indicated.
  • 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.
  • the outlet of the transition channels 201 corresponds to the narrowest flow cross-section of the mixing tube 220.
  • the said transition channels 201 therefore bridge the respective cross-sectional difference without adversely affecting the flow formed.
  • a diffuser (not shown in the figure) at the end of the mixing tube.
  • 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 a central backflow zone 50 form, which has the properties of a flame holder. If 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.
  • This consists of two hollow ones conical partial bodies 101, 102 which are nested in one another offset.
  • the number of conical partial bodies can of course be greater than two, as shown in FIGS. 4 and 5; This depends on the mode of operation 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 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 tapered body 101, 102 furthermore 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, as shown by the arrows 116 want.
  • 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.
  • liquid fuels should be supplied via lines 108, 109.
  • the conical partial bodies 101, 102 with respect to the cone angle and the width of the tangential air inlet slots 119, 120, strict limits must be observed per se so that the desired flow field of the combustion air 115 can be set at the outlet of the swirl generator 100.
  • a downsizing of the tangential air inlet slots 119, 120 favors the faster formation of a backflow zone already in the area of the swirl generator.
  • the axial speed within the swirl generator 100 can be changed by a corresponding supply, not shown, of an axial combustion air flow.
  • a corresponding swirl generation 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 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, by having a fixed component as required form 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 works on a principle different from that described under FIG. 2. is constructed.
  • the surface of the individual transition channels 201 which runs downward in the flow direction has a shape which runs spirally in the flow direction and which describes a crescent-shaped course, corresponding to 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.

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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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Air Supply (AREA)
EP95810587A 1994-10-01 1995-09-20 Brûleur Expired - Lifetime EP0704657B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4435266 1994-10-01
DE4435266A DE4435266A1 (de) 1994-10-01 1994-10-01 Brenner

Publications (3)

Publication Number Publication Date
EP0704657A2 true EP0704657A2 (fr) 1996-04-03
EP0704657A3 EP0704657A3 (fr) 1997-07-30
EP0704657B1 EP0704657B1 (fr) 2001-11-07

Family

ID=6529801

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810587A Expired - Lifetime EP0704657B1 (fr) 1994-10-01 1995-09-20 Brûleur

Country Status (8)

Country Link
US (1) US5588826A (fr)
EP (1) EP0704657B1 (fr)
JP (1) JP3649785B2 (fr)
KR (1) KR960014753A (fr)
CN (1) CN1090728C (fr)
AT (1) ATE208480T1 (fr)
CA (1) CA2154941A1 (fr)
DE (2) DE4435266A1 (fr)

Cited By (62)

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EP0833104A2 (fr) 1996-09-25 1998-04-01 Abb Research Ltd. Brûleur pour le fonctionnement d'une chambre de combustion
EP0797051A3 (fr) * 1996-03-20 1998-05-20 Abb Research Ltd. Brûleur pour un générateur de chaleur
EP0845639A1 (fr) 1996-11-29 1998-06-03 Abb Research Ltd. Chambre de combustion
EP0851172A2 (fr) 1996-12-23 1998-07-01 Abb Research Ltd. Brûleur pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide ou gazeux
EP0780630A3 (fr) * 1995-12-21 1998-07-29 Abb Research Ltd. Brûleur pour un générateur de chaleur
EP0780629A3 (fr) * 1995-12-21 1998-08-19 ABB Research Ltd. Brûleur pour un générateur de chaleur
EP0833105A3 (fr) * 1996-09-30 1998-10-21 Abb Research Ltd. Brûleur à prémélange
EP0899508A1 (fr) * 1997-08-25 1999-03-03 Abb Research Ltd. Brûleur pour un dispositif à chaleur
EP0902233A1 (fr) 1997-09-15 1999-03-17 Abb Research Ltd. Buse de pulvérisation par pression combinée
EP0924461A1 (fr) 1997-12-22 1999-06-23 Abb Research Ltd. Buse de pulvérisation par pression à deux étages
EP0924460A1 (fr) 1997-12-22 1999-06-23 Abb Research Ltd. Buse de pulvérisation par pression à deux étages
US5954496A (en) * 1996-09-25 1999-09-21 Abb Research Ltd. Burner for operating a combustion chamber
US6106278A (en) * 1997-05-17 2000-08-22 Abb Research Ltd. Combustion chamber
US6192669B1 (en) 1997-03-20 2001-02-27 Asea Brown Boveri Ag Combustion chamber of a gas turbine
EP0892219B1 (fr) * 1997-07-15 2002-10-23 Alstom Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbines à gaz
DE10160907A1 (de) * 2001-12-12 2003-08-14 Alstom Switzerland Ltd Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner
EP1389713A1 (fr) 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
DE19912701B4 (de) * 1999-03-20 2006-01-19 Alstom Brennkammerwand
DE19654009B4 (de) * 1996-12-21 2006-05-18 Alstom Vormischbrenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff
US7082768B2 (en) 2001-12-20 2006-08-01 Alstom Technology Ltd Method for injecting a fuel-air mixture into a combustion chamber
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
WO2009019113A2 (fr) 2007-08-07 2009-02-12 Alstom Technology Ltd Brûleur pour une chambre de combustion d'un turbogroupe
US7491056B2 (en) 2004-11-03 2009-02-17 Alstom Technology Ltd. Premix burner
EP2068076A2 (fr) 2007-12-03 2009-06-10 Siemens Aktiengesellschaft Améliorations portant sur ou en relation avec des brûleurs pour un moteur à turbine à gaz
WO2009019114A3 (fr) * 2007-08-07 2009-06-11 Alstom Technology Ltd Combustible pour une chambre de combustion d'un turbogroupe
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US7780437B2 (en) 2004-10-11 2010-08-24 Stefano Bernero Premix burner
WO2010115980A2 (fr) 2009-04-11 2010-10-14 Alstom Technology Ltd. Chambre de combustion dotée d'un amortisseur de helmholtz
WO2011026732A1 (fr) 2009-09-03 2011-03-10 Alstom Technology Ltd. Groupe turbine à gaz
EP2299178A1 (fr) 2009-09-17 2011-03-23 Alstom Technology Ltd Procédé et système de combustion de turbine à gaz pour mélanger sans danger des carburants riches en H2 avec de l'air
US7972133B2 (en) 2006-03-27 2011-07-05 Alstom Technology Ltd. Burner for the operation of a heat generator and method of use
US8033821B2 (en) 2007-11-27 2011-10-11 Alstom Technology Ltd. Premix burner for a gas turbine
US8057224B2 (en) 2004-12-23 2011-11-15 Alstom Technology Ltd. Premix burner with mixing section
US8210797B2 (en) 2008-05-26 2012-07-03 Alstom Technology Ltd Gas turbine with a stator blade
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WO2012136787A1 (fr) 2011-04-08 2012-10-11 Alstom Technology Ltd Ensemble de turbines à gaz et procédé permettant de faire fonctionner celui-ci
US8413449B2 (en) 2008-02-20 2013-04-09 Alstom Technology Ltd Gas turbine having an improved cooling architecture
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US8468833B2 (en) 2008-03-07 2013-06-25 Alstom Technology Ltd Burner arrangement, and use of such a burner arrangement
WO2014001230A1 (fr) 2012-06-29 2014-01-03 Alstom Technology Ltd Procédé pour une opération de réduction de co de charge partielle pour une turbine à gaz séquentielle
EP2685172A2 (fr) 2012-07-09 2014-01-15 Alstom Technology Ltd Système de combustion de turbine à gaz de type tubo-annulaire avec de la combustion pré-mélangé étagée
EP2685161A1 (fr) 2012-07-10 2014-01-15 Alstom Technology Ltd Agencement de chambre de combustion, en particulier pour turbine à gaz
EP2700878A2 (fr) 2012-08-24 2014-02-26 Alstom Technology Ltd Procédé pour mélanger un air de dilution dans un système de combustion séquentielle d'une turbine à gaz
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EP2703721A1 (fr) 2012-08-31 2014-03-05 Alstom Technology Ltd Brûleur à prémélange
EP2725300A1 (fr) 2012-10-24 2014-04-30 Alstom Technology Ltd Dispositif d'amortissement pour réduire les pulsations de chambres de combustion
US8783044B2 (en) 2007-12-29 2014-07-22 Alstom Technology Ltd Turbine stator nozzle cooling structure
US8801366B2 (en) 2008-03-28 2014-08-12 Alstom Technology Ltd. Stator blade for a gas turbine and gas turbine having same
EP2796789A1 (fr) 2013-04-26 2014-10-29 Alstom Technology Ltd Chambre de combustion à tubes pour un agencement de chambre de combustion annulaire dans une turbine à gaz
US20140318107A1 (en) * 2012-08-08 2014-10-30 Hino Motors, Ltd. Burner for exhaust purifying device
US8950192B2 (en) 2008-02-20 2015-02-10 Alstom Technology Ltd. Gas turbine
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US10208960B2 (en) 2007-11-27 2019-02-19 Ansaldo Energia Switzerland AG Method for operating a gas turbine installation and equipment for carrying out the method

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EP0704657A3 (fr) 1997-07-30
CA2154941A1 (fr) 1996-04-02
CN1090728C (zh) 2002-09-11
CN1131737A (zh) 1996-09-25
JPH08114307A (ja) 1996-05-07
ATE208480T1 (de) 2001-11-15
US5588826A (en) 1996-12-31
KR960014753A (ko) 1996-05-22
DE4435266A1 (de) 1996-04-04
JP3649785B2 (ja) 2005-05-18
EP0704657B1 (fr) 2001-11-07
DE59509802D1 (de) 2001-12-13

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