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US20070042307A1 - Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber - Google Patents

Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber Download PDF

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Publication number
US20070042307A1
US20070042307A1 US11/503,163 US50316306A US2007042307A1 US 20070042307 A1 US20070042307 A1 US 20070042307A1 US 50316306 A US50316306 A US 50316306A US 2007042307 A1 US2007042307 A1 US 2007042307A1
Authority
US
United States
Prior art keywords
premix burner
inside wall
flow
cone shell
swirl
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.)
Abandoned
Application number
US11/503,163
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English (en)
Inventor
Elena De Marcos
Christian Steinbach
Nicolas Ulibarri
Martin Von Planta
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Assigned to ALSTOM TECHNOLOGY LTD. reassignment ALSTOM TECHNOLOGY LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DE MARCOS, ELENA, ULIBARRI, NICOLAS, VON PLANTA, MARTIN ANDREA, STEINBACH, CHRISTIAN
Publication of US20070042307A1 publication Critical patent/US20070042307A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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 
    • 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

  • a premixer for operating a combustion chamber with a gaseous and/or liquid fuel, having a swirl generator for inducing a swirl flow in an incoming combustion air flow and means for injecting fuel into the swirl flow, the swirl generator having at least two cone shell segments which fit together to form a flow body and together enclose a conically formed swirl space with a cone angle ⁇ and air inlet slits directed tangentially to the length of the cone.
  • Premix burners of the aforementioned generic type are known from many prior publications, such as for example from EP 0 210 462 A1 and EP 0 321 809 B1, the contents of which are hereby incorporated by reference in their entireties, to mention just two.
  • Premix burners of this type are based on the general operating principle of generating within a generally conically formed swirl generator, which provides at least two cone shell segments fitted together in such a way that they appropriately overlap one another, a swirl flow which comprises a mixture of fuel and air and is ignited within a combustion chamber downstream of the premix burner in the direction of flow, thereby forming a premix flame which is spatially as stable as possible.
  • the spatial position of the premix flame is determined by the aerodynamic behavior of the swirl flow, the swirl coefficient of which increases with increasing propagation along the burner axis, consequently becomes unstable and ultimately, as the result of a discontinuous cross-sectional transition between the burner and the combustion chamber, breaks down into an annular swirl flow with the formation of a backflow zone, in the forward region of which, in the direction of flow, the premix flame forms.
  • the aerodynamic stability of the backflow zone forming depends on the design, shape and size of the swirl generator. For example, if the forwardmost front in the direction of flow of the backflow zone forming is not spatially stabilized successfully, thermoacoustic vibrations or pulsations can occur to an increased extent within the combustion system, impairing the overall combustion and the release of heat.
  • premix burner systems previously known and in use are restricted to overall sizes in which the maximum burner diameter at the burner outlet is only 180 mm.
  • Premix burners of this type additionally have a relatively pointed, i.e. small, cone angle, of less than or equal to 18°, so that the length of the burner tends to be great in relation to the diameter of the burner facing downstream, but is still well able to be handled for assembly and maintenance purposes.
  • the aim is to replace the previously operated single diffusion burners that are primarily used for firing silo combustion chambers of large dimensions by more modern, environmentally more acceptable burner systems.
  • a further very important and at the same time critical aspect of a desired increase in size or increase in output of the previously known premix burner systems concerns the downstream termination of the cone shell segments enclosing the swirl space of the swirl generator, which in the example of the double cone burner described in EP 0 321 809 B1 end in axially directed blocking-off elements.
  • These blocking-off elements contribute to the formation of undesired separation vortices which, as coherent vortex structures, lead to combustion instabilities and, associated therewith, to thermoacoustic vibrations or pulsations.
  • premix burner arrangements for example U.S. Pat. No. 5,588,826, also incorporated herein by reference
  • a transitional geometry interposed between the swirl generator and the combustion chamber for example in the form of a hollow-cylindrically formed mixing tube.
  • transitional geometries of this type are extremely sensitive aerodynamically, since flow separations in this zone can lead to flashback or spontaneous ignition.
  • transitional geometries of this type contribute decisively to the production costs.
  • a premix burner is disclosed wherein, in spite of the increase in size of the burner dimensions, the optimized burner properties in the case of previously known premix burners can be retained virtually unchanged.
  • the aim is to increase the size of the burner of previously known premix burner systems can be increased in order to reduce the number of burners in multiple burner arrangements, as described at the beginning, and also to reduce the associated system costs.
  • previously known single diffusion burners as are used for example for the firing of silo combustion chambers, can be replaced by a single premix burner.
  • a premix burner is developed in such a way that, at least at the downstream end region of the swirl generator, a shaped element enclosing the cone shell segments with an inside wall facing the cone shell segments is provided, and the cone shell segments end in the inside wall in a flush manner while maintaining their shape.
  • the concept of “maintaining their shape” means for the purposes of the invention that the shape of the cone shell segments formed in the manner of segments of a cone remains unchanged in the region where they come into contact with the inside wall of the shaped element enclosing the cone shell segments, as though the cone shell segments would penetrate unhindered through the shaped element in a radially outward direction.
  • the inside wall of the shaped element also serves for forming a flow channel adjoining the cone shell segments downstream.
  • it also serves as a mixing tube or as a joining element, in the sense of a flanged piece, by means of which the swirl generator can be connected to a combustion chamber following on in the direction of flow, such as for example a silo combustion chamber, or some other channel structure.
  • cone angles of at least 11°, but preferably in the range of 20° and greater, are used, at which angles the cone shell segments surround the swirl space in a conically widening manner.
  • burners with a burner diameter in the outlet region of greater than 500 mm which have a burner length of well below one meter can be made possible.
  • FIGS. 1 and 2 show a perspective representation of an exemplary premix burner with a cylindrically formed shaped element
  • FIGS. 3 and 4 show a perspective representation of an exemplary premix burner with a frustoconically formed shaped element
  • FIG. 5 shows a sectional representation through an exemplary premix burner with a frustoconically formed shaped element
  • FIGS. 6 and 7 show a perspective representation of an exemplary premix burner with a shaped element having an inlet region formed in a funnel-shaped manner.
  • FIG. 1 Shown in FIG. 1 is a perspective representation of a premix burner, with the viewing direction from the downstream side into the swirl space of a swirl generator 2 that is enclosed by a multiplicity of cone shell segments 1 .
  • FIG. 2 shows the same premix burner, but from a different viewing angle, that is looking at the swirl generator 2 from the outside, said generator being enclosed by eight cone shell segments 1 in the exemplary embodiment represented.
  • the further refinements of the exemplary embodiment represented in FIGS. 1 and 2 are the same in each case, so that there is no further distinction between FIG. 1 and FIG. 2 .
  • the premix burner represented has a central receiving unit 3 , which takes the form of a receiving sleeve and is intended for a central fuel supply unit, for example in the form of a fuel nozzle for liquid fuels or fuel lance for a pilot flame (not represented), to be pushed in and held.
  • the cone shell segments 1 connected by their upstream ends to the receiving unit 3 , mutually enclose air inlet slits 4 and are placed with respect to a burner axis A extending centrally through the premix burner in such a way that they delimit a swirl space widening conically in the direction of flow at a cone angle ⁇ .
  • Each individual cone shell segment 1 has, moreover, depending on the type of fuel, at least one fuel supply line 5 , by means of which fuel can be admixed into the incoming combustion air flow passing through the air inlet slits 2 .
  • the individual cone shell segments 1 While maintaining their shape, the individual cone shell segments 1 open out with their downstream end on an inside wall 6 of a cylindrically formed shaped element 7 surrounding the cone shell segments 1 .
  • the individual cone shell segments 1 are connected to the inside wall 6 of the shaped element 7 along a line of intersection 8 , which is obtained by a virtual penetration of each individual cone shell segment 1 with the inside wall 6 of the cylindrical shaped element 7 . In this way, the swirl flow formed inside the swirl generator 2 does not undergo any disturbance after flowing over the individual cone shell segments 1 .
  • a second shaped element 9 Provided upstream of the shaped element 7 , for purposes of an improved incoming air flow through the air inlet slits 4 of the swirl generator 2 , is a second shaped element 9 , which is likewise formed in a hollow-cylindrical manner and has a greater inside diameter than the first shaped element 7 .
  • the transition between the inside diameters of the shaped elements 7 and 9 takes place by means of a discontinuous stage 10 , which is adjoined, moreover, by the fuel supply lines 5 of each individual cone shell segment 1 .
  • the downstream contour of the shaped element 7 is formed in a cylindrical manner and offers the possibility of a constructionally simple connection, for example to a combustion chamber (not represented) arranged downstream in the direction of flow of the premix burner represented.
  • FIGS. 3 and 4 Shown in a perspective representation in FIGS. 3 and 4 is a further exemplary embodiment of a premix burner formed according to the invention, in which, as a difference from the exemplary embodiment that is represented in FIGS. 1 and 2 , the region of the shaped element 7 is formed as a frustoconical portion tapering conically in the direction of flow. To avoid repetition, the reference numerals that have already been introduced are not described.
  • the exemplary embodiment represented in FIGS. 3 and 4 has in the region of the shaped element 7 an inside wall 6 , which is hatched in the perspective representations and is adjoined by the downstream ends of the cone shell segments 1 , while maintaining their shape.
  • Adjoining the inside wall 6 of the shaped element 7 downstream is a shaped element 11 which is formed in a hollow-cylindrical manner and serves as a coupling piece or flanged piece for a following combustion chamber.
  • the inside wall 6 placed with respect to the cone shell segments 1 has the effect that the lines of intersection 8 of the cone shell segments 1 with which they adjoin the inside wall 6 are smaller or shorter in the direction of flow than in the case of the aforementioned exemplary embodiment, in which the cone shell segments adjoin along a cylindrically formed inside wall directed coaxially in relation to the burner axis.
  • FIG. 5 A graphic cross-sectional representation of the embodiment shown in FIGS. 3 and 4 can be seen in FIG. 5 .
  • shape-maintaining adjoinment of each individual cone shell segment 1 to the inside wall 6 of the shaped element 7 tapering conically in the direction of flow in the form of a cone, which element goes over in the direction of flow into a straight-cylindrical region 11 .
  • FIGS. 6 and 7 Depicted in FIGS. 6 and 7 is a further exemplary embodiment of a premix burner, provided with a shaped element 7 which has an upstream region, the so-called inflow region 12 , which has an inside wall 6 tapering in the form of a funnel in the direction of flow.
  • the curvature of the inside wall 6 in this inflow region 12 corresponds approximately to the contour of a quarter ellipse.
  • the inflow region 12 is adjoined in the direction of flow as part of the shaped element 7 by a flow region 12 ′ with a largely constant flow cross section, to which finally an inlet flange of a combustion chamber can be attached (not represented).
  • the cone shell segments 1 of the swirl generator 2 end in the adjoining inside wall 6 of the shaped element 7 in a flush manner, as though the cone shell segments would penetrate unhindered through the inside wall 6 , but the cone shell segments 1 terminate respectively by means of the lines of intersection 8 at the inside wall 6 .
  • the downstream end regions of the cone shell segments 1 closely follow the elliptical curvature of the inside wall 6 in this region 12 .
  • each individual cone shell segment by its downstream end region to an inside wall of a shaped element surrounding the cone shell segments, while maintaining its shape, leads to minimal irritation of the swirl flow passing through the cone shell segments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Feeding And Controlling Fuel (AREA)
US11/503,163 2004-02-12 2006-08-14 Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber Abandoned US20070042307A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH2102004 2004-02-12
CH00210/04 2004-02-12
PCT/EP2005/050579 WO2005078348A1 (de) 2004-02-12 2005-02-09 Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2005/050579 Continuation WO2005078348A1 (de) 2004-02-12 2005-02-09 Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer

Publications (1)

Publication Number Publication Date
US20070042307A1 true US20070042307A1 (en) 2007-02-22

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Family Applications (1)

Application Number Title Priority Date Filing Date
US11/503,163 Abandoned US20070042307A1 (en) 2004-02-12 2006-08-14 Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber

Country Status (10)

Country Link
US (1) US20070042307A1 (de)
EP (1) EP1714081B1 (de)
CN (1) CN1942710A (de)
AT (1) ATE391887T1 (de)
BR (1) BRPI0507640A (de)
CA (1) CA2555481A1 (de)
DE (1) DE502005003648D1 (de)
MX (1) MXPA06008994A (de)
MY (1) MY141577A (de)
WO (1) WO2005078348A1 (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080032246A1 (en) * 2005-03-09 2008-02-07 Thomas Ruck Premixing Burner for Generating an Ignitable Fuel/Air Mixture
US20090139240A1 (en) * 2007-09-13 2009-06-04 Leif Rackwitz Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
US20120178035A1 (en) * 2011-01-11 2012-07-12 Wei-Long Chen Device for Producing Stable and Augmented Flame
US20130011800A1 (en) * 2011-07-06 2013-01-10 Wei-Long Chen Flame Device Including a Lift Mechanism and can Lift a Flame to a Predetermined Height
EP2685160A1 (de) * 2012-07-10 2014-01-15 Alstom Technology Ltd Multikonus-Vormischungsbrenner für eine Gasturbine
JP2014016151A (ja) * 2012-07-10 2014-01-30 Alstom Technology Ltd ガスタービンバーナ用の軸方向スワーラ
JP2014048040A (ja) * 2012-08-31 2014-03-17 Alstom Technology Ltd 予混合バーナ
US20150007571A1 (en) * 2012-03-29 2015-01-08 Alstom Technology Ltd Gas turbine combustor
US20150153066A1 (en) * 2013-12-04 2015-06-04 Victory Energy Operations. L.L.C. Method of providing heat to a heat exchanger apparatus via a burner
US9933163B2 (en) * 2012-07-10 2018-04-03 Ansaldo Energia Switzerland AG Combustor arrangement with slidable multi-cone premix burner

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1856447B1 (de) 2005-03-09 2014-09-24 Alstom Technology Ltd Vormischbrenner zum betreiben einer brennkammer
CN101709884B (zh) * 2009-11-25 2012-07-04 北京航空航天大学 一种预混预蒸发燃烧室
US8813967B2 (en) * 2012-05-02 2014-08-26 Alstom Technology Ltd Adjustable mill classifier
EP2685163B1 (de) 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Multikonus-Vormischungsbrenner für eine Gasturbine
DE102021002508A1 (de) * 2021-05-12 2022-11-17 Martin GmbH für Umwelt- und Energietechnik Düse zum Einblasen von Gas in eine Verbrennungsanlage mit einem Rohr und einem Drallerzeuger, Rauchgaszug mit einer derartigen Düse und Verfahren zur Verwendung einer derartigen Düse

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US5588826A (en) * 1994-10-01 1996-12-31 Abb Management Ag Burner
US5823764A (en) * 1996-10-08 1998-10-20 Ansaldo Energia S.P.A. Three-stage low NOx burner for burning solid, liquid and gaseous fuels
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US5934555A (en) * 1996-03-05 1999-08-10 Abb Research Ltd. Pressure atomizer nozzle
US5944507A (en) * 1997-05-07 1999-08-31 The Boc Group Plc Oxy/oil swirl burner
US5980240A (en) * 1997-12-22 1999-11-09 Asea Brown Boveri Ag Burner
US6004097A (en) * 1997-09-26 1999-12-21 Sure Alloy Steel Corp. Coal mill exhauster fan
US6102692A (en) * 1997-08-25 2000-08-15 Abb Alstom Power (Switzerland) Ltd Burner for a heat generator
US6119459A (en) * 1998-08-18 2000-09-19 Alliedsignal Inc. Elliptical axial combustor swirler
US20020026796A1 (en) * 2000-08-21 2002-03-07 Ephraim Gutmark Method for increasing the fluid-mechanical stability of a premix burner as well as a premix burner for performing the method
US6502399B2 (en) * 1997-09-10 2003-01-07 Mitsubishi Heavy Industries, Ltd. Three-dimensional swirler in a gas turbine combustor
US6702574B1 (en) * 1998-12-23 2004-03-09 Alstom (Schweiz) Ag Burner for heat generator
US7070637B1 (en) * 2003-01-21 2006-07-04 The Board Of Trustees Of The University Of Illinois Apparatus for separating particles from a fluid
US7241138B2 (en) * 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection

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DE19527453B4 (de) * 1995-07-27 2009-05-07 Alstom Vormischbrenner
EP0985877A1 (de) * 1998-09-10 2000-03-15 Abb Research Ltd. Vorrichtung und Verfahren zur Minimierung thermoakustischer Schwingungen in Gasturbinenbrennkammern
DE10049205A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2166276A (en) * 1937-10-06 1939-07-18 American Blower Corp Tunnel fan
US3677013A (en) * 1969-12-29 1972-07-18 Snecma Device for burning the unburnt residue in the exhaust gases of internal combustion engines
US3845903A (en) * 1973-08-15 1974-11-05 Dunham Bush Inc One piece radial vane diffuser and method of manufacturing the same
US4047879A (en) * 1975-06-27 1977-09-13 Canadian Patents And Development Limited Oil burner assembly
US4297093A (en) * 1978-09-06 1981-10-27 Kobe Steel, Ltd. Combustion method for reducing NOx and smoke emission
US4464108A (en) * 1980-11-21 1984-08-07 Donald Korenyi Combustion apparatus
US4479775A (en) * 1981-12-04 1984-10-30 Sivan Development And Implementation Of Technological Systems Ltd. Vane structure burner for improved air-fuel combustion
US4695225A (en) * 1983-08-30 1987-09-22 Bbc Brown, Boveri & Company, Limited Axial swirl body for generating rotary flows
US5489202A (en) * 1992-11-09 1996-02-06 Foster Wheeler Energy Corporation Vibration of systems comprised of hot and cold components
US5470224A (en) * 1993-07-16 1995-11-28 Radian Corporation Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels
US5573392A (en) * 1994-07-13 1996-11-12 Abb Research Ltd. Method and device for distributing fuel in a burner suitable for both liquid and gaseous fuels
US5588826A (en) * 1994-10-01 1996-12-31 Abb Management Ag Burner
US5586878A (en) * 1994-11-12 1996-12-24 Abb Research Ltd. Premixing burner
US5876196A (en) * 1995-12-21 1999-03-02 Abb Research Ltd. Burner for a heat generator
US5934555A (en) * 1996-03-05 1999-08-10 Abb Research Ltd. Pressure atomizer nozzle
US5823764A (en) * 1996-10-08 1998-10-20 Ansaldo Energia S.P.A. Three-stage low NOx burner for burning solid, liquid and gaseous fuels
US5944507A (en) * 1997-05-07 1999-08-31 The Boc Group Plc Oxy/oil swirl burner
US6102692A (en) * 1997-08-25 2000-08-15 Abb Alstom Power (Switzerland) Ltd Burner for a heat generator
US6502399B2 (en) * 1997-09-10 2003-01-07 Mitsubishi Heavy Industries, Ltd. Three-dimensional swirler in a gas turbine combustor
US6004097A (en) * 1997-09-26 1999-12-21 Sure Alloy Steel Corp. Coal mill exhauster fan
US5980240A (en) * 1997-12-22 1999-11-09 Asea Brown Boveri Ag Burner
US6119459A (en) * 1998-08-18 2000-09-19 Alliedsignal Inc. Elliptical axial combustor swirler
US6702574B1 (en) * 1998-12-23 2004-03-09 Alstom (Schweiz) Ag Burner for heat generator
US20020026796A1 (en) * 2000-08-21 2002-03-07 Ephraim Gutmark Method for increasing the fluid-mechanical stability of a premix burner as well as a premix burner for performing the method
US7241138B2 (en) * 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
US7070637B1 (en) * 2003-01-21 2006-07-04 The Board Of Trustees Of The University Of Illinois Apparatus for separating particles from a fluid

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8007273B2 (en) * 2005-03-09 2011-08-30 Alstom Technology Ltd. Premixing burner for generating an ignitable fuel/air mixture
US20080032246A1 (en) * 2005-03-09 2008-02-07 Thomas Ruck Premixing Burner for Generating an Ignitable Fuel/Air Mixture
US8646275B2 (en) 2007-09-13 2014-02-11 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
US20090139240A1 (en) * 2007-09-13 2009-06-04 Leif Rackwitz Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
US20120178035A1 (en) * 2011-01-11 2012-07-12 Wei-Long Chen Device for Producing Stable and Augmented Flame
US8641413B2 (en) * 2011-01-11 2014-02-04 Pro-Iroda Industries, Inc. Device for producing stable and augmented flame
US20130011800A1 (en) * 2011-07-06 2013-01-10 Wei-Long Chen Flame Device Including a Lift Mechanism and can Lift a Flame to a Predetermined Height
US20150007571A1 (en) * 2012-03-29 2015-01-08 Alstom Technology Ltd Gas turbine combustor
JP2014016151A (ja) * 2012-07-10 2014-01-30 Alstom Technology Ltd ガスタービンバーナ用の軸方向スワーラ
EP2685160A1 (de) * 2012-07-10 2014-01-15 Alstom Technology Ltd Multikonus-Vormischungsbrenner für eine Gasturbine
US8950187B2 (en) 2012-07-10 2015-02-10 Alstom Technology Ltd Premix burner of the multi-cone type for a gas turbine
US9518740B2 (en) 2012-07-10 2016-12-13 General Electric Company Gmbh Axial swirler for a gas turbine burner
US9933163B2 (en) * 2012-07-10 2018-04-03 Ansaldo Energia Switzerland AG Combustor arrangement with slidable multi-cone premix burner
JP2014048040A (ja) * 2012-08-31 2014-03-17 Alstom Technology Ltd 予混合バーナ
US20150153066A1 (en) * 2013-12-04 2015-06-04 Victory Energy Operations. L.L.C. Method of providing heat to a heat exchanger apparatus via a burner

Also Published As

Publication number Publication date
DE502005003648D1 (de) 2008-05-21
CN1942710A (zh) 2007-04-04
ATE391887T1 (de) 2008-04-15
MY141577A (en) 2010-05-14
MXPA06008994A (es) 2006-12-14
WO2005078348A1 (de) 2005-08-25
BRPI0507640A (pt) 2007-07-10
EP1714081A1 (de) 2006-10-25
CA2555481A1 (en) 2005-08-25
EP1714081B1 (de) 2008-04-09

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