EP1828684A1 - Bruleur de premelange dote d'un parcours de melange - Google Patents

Bruleur de premelange dote d'un parcours de melange

Info

Publication number
EP1828684A1
EP1828684A1 EP05804628A EP05804628A EP1828684A1 EP 1828684 A1 EP1828684 A1 EP 1828684A1 EP 05804628 A EP05804628 A EP 05804628A EP 05804628 A EP05804628 A EP 05804628A EP 1828684 A1 EP1828684 A1 EP 1828684A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
swirl
mixing tube
premix burner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP05804628A
Other languages
German (de)
English (en)
Inventor
Hans Peter KNÖPFEL
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.)
Ansaldo Energia Switzerland AG
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
Publication of EP1828684A1 publication Critical patent/EP1828684A1/fr
Withdrawn legal-status Critical Current

Links

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 conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2201/00—Staged combustion
    • F23C2201/20—Burner staging
    • 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 invention relates to a premix burner with a mixing section for a heat generator, preferably for a combustion chamber for operating a gas turbine plant, with complementary to a swirler Operakegelschalen spanning a conically expanding swirl space and mutually tangential air inlet slots along which supply gaseous fuel are provided distributed, with at least one along a swirl space centrally passing through the burner axis arranged fuel supply for liquid fuel and with a downstream of the swirl body via a transition piece subsequent mixing tube.
  • a premix burner without a mixing tube can be found in EP 0 321 809 B1, which is incorporated herein by reference
  • Substantially consists of two hollow, conical, nested in the flow direction part bodies, whose respective longitudinal axes of symmetry are offset from each other, so that the adjacent walls of the body part in their longitudinal extent form tangential slots for a combustion air flow.
  • liquid fuel is injected into the swirl space enclosed by the partial bodies via a central nozzle, while gaseous fuel is introduced via the further nozzles present in the region of the tangential air inlet slots in the longitudinal extent.
  • the burner concept of the premix burner mentioned above is based on the generation of a closed swirl flow within the conically expanding swirl space.
  • the swirl flow becomes unstable within the swirl space and changes into an annular swirl flow with a backflow zone in the flow core.
  • the location at which the swirling flow passes through bursting into an annular swirling flow with a backflow zone to form a so-called backflow bubble is determined essentially by the cone angle, which is inscribed by the partial cone shells, and the slot width of the air inlet slots.
  • narrow limits are set in the choice for dimensioning the slot width and the cone angle, which ultimately determines the overall length of the burner, so that a desired flow field can be established, which leads to the formation of a swirl flow, in the burner mouth region in an annular swirling under Formation of a spatially stable remindströmzone bursts, in which ignites the fuel-air mixture to form a spatially stable flame.
  • a reduction of the air inlet slots leads to an upstream displacement of the remindströmzone, whereby then, however, the mixture of fuel and air in time and spatially earlier comes to the ignition.
  • a mixing section in the form of a mixing tube which continues the swirl flow is provided downstream of the swirl body, as described, for example, in EP 0 704 657 B1 in US Pat Individual described.
  • a swirl body consisting of four partial cone bodies can be seen, at which downstream a mixing section serving for a further mixing of the fuel-air mixture follows.
  • transition channels extending in the flow direction between the swirl body and the mixing section are provided, which serve to transfer the swirl flow formed in the swirl body into the mixing section downstream of the transition channels.
  • the invention has the object of providing a premix burner with downstream mixing section for a heat generator, in particular for firing a combustor to drive a gas turbine plant with complementary to a swirler Operakegelschalen that span a conically expanding swirl space and limit each other tangential air inlet slots, along which Distributions are provided for gaseous fuel distributed, with at least one along a twisting space passing through the burner axis arranged fuel supply for liquid fuel and with a downstream of the swirl body via a transition piece subsequent mixing tube, such that its use even with larger-sized gas turbine plants, the one require greater burner load, is possible without having to change the design of the premix burner significantly.
  • a further object is to provide a method for operating a premixing burner with downstream mixing path for a heat generator, in particular for firing a combustion chamber for driving a gas turbine plant, which makes it possible to stabilize the flame position despite increasing the premix burner, the CO, UHC and reduce NO ⁇ emissions, reduce combustion chamber pulsations that occur, and increase the stability range.
  • the burnout should be complete.
  • the solution of the problem underlying the invention is specified in claim 1.
  • a method according to the solution is specified in claim 10.
  • the concept of the invention advantageously further features are the subject of the dependent claims and the description in particular with reference to the exemplary embodiments.
  • a premix burner with a downstream mixing section in the form of a mixing tube is formed in that at least one further fuel supply is provided in the region of the swirler, the transition piece and / or the mixing tube, which makes it possible radially from the outside with respect to Feeding fuel into the fuel-air mixture in the direction of flow within the burner forming swirl flow.
  • the solution according to additional fuel feed which may consist of a liquid fuel, from areas of the burner housing, which comprises radially extending in the form of a swirl flow along the burner axis fuel-air mixture, the radial fuel gradient is so far counteracted by the fuel concentration in the radial axis to the burner remote flow areas is raised by metered fuel feed until a desired fuel profile along a flow cross-section is established.
  • At least two, preferably a plurality of individual fuel feed points axially symmetrical to the burner axis in the respective burner housing areas be it swirl body, transition piece and / or mixing tube provided.
  • the fuel feeds are preferably as Liquid fuel nozzles formed by the liquid fuel to form a fuel spray can be discharged, and it is readily possible to introduce other fuels.
  • the degree of atomization must be selected by providing appropriate nozzle contours.
  • the fuel nozzle may be formed as a mere hole nozzle, through which the fuel is introduced in the form of a fuel jet.
  • the angle relative to the burner axis under which the fuel is introduced radially from the outside into the swirl flow between 90 °, i. the fuel entry is perpendicular to the burner axis, and a larger angle up to a maximum of 180 °, i. the fuel input is parallel to the burner axis in the flow direction of the swirl flow to choose.
  • an additional fuel feed in the region of the mixing tube which may have a rectilinear hollow cylindrical inner wall or a contoured inner wall in the manner of a diffusive structure.
  • the mass flows of the fuel supplied to the burner to optimize the burner flow field become.
  • the fuel addition is to be selected accordingly both via the central fuel burner oriented along the burner axis and via the further fuel feeds provided radially around the burner axis in the burner housing in order to obtain the most homogeneous fuel-air mixture in the entire flow cross-section.
  • the first stage corresponds to the central fuel supply and the second stage of the radially in the flow field inwardly directed fuel supply, a the respective Operationsg. Last point of the gas turbine plant optimally adapted distribution of the fuel can be achieved, which leads to low emissions, lower pulsations and thus also to a larger operating range of the burner.
  • FIGS. 1 to 4 show longitudinal cross sections through a burner arrangement with a cone-shaped premix burner 1, adjoined downstream of the burner axis A by a transition piece 2, which in turn is connected downstream to a mixing tube 3.
  • a mixing tube 3 is not shown in Figures 1 to 4 a downstream of the mixing tube 3 to be provided combustion chamber, which serves to drive a gas turbine plant.
  • the premix burner 1 shown in FIGS. 1 to 4 is designed as a double-cone burner known per se and delimits with two partial cone shells 5 a swirl space 6 which expands conically along the burner axis A in the flow direction (see arrow illustration) in the area of the smallest internal cross section of the conically widening Swirl chamber 6 is provided axially to the burner axis A, a central liquid fuel nozzle 11, through which a fuel spray 12 which propagates substantially symmetrically to the burner axis A is formed.
  • combustion air L passes with a directed to the burner axis A spin into the swirl chamber 6, which mixes with gaseous fuel, which is distributed longitudinally to the air inlet slots 7 arranged fuel supply 8 is discharged.
  • the representation of the mixing tube 4 is shown for reasons of a simplified graphical representation with two differently shaped half-planes, each representing different mixing tubes.
  • the mixing tube 4 has a contoured inner wall, which is designed in the manner of a diffuser, with a flow cross section which tapers in the direction of flow and has a smallest and an enlarged cross section.
  • the lower half of the mixing tube 4 shown in longitudinal cross-sectional representation represents a mixing tube with a straight cylinder-shaped inner wall.
  • the mixing tube according to the upper image representation with A1, A2, A3 and A4 whereas the mixing tube according to the lower alternative embodiment is respectively denoted by B1, B2, B3 and B4 ,
  • a further fuel feed 13 is provided in the region of the mixing tube 4, through which a fuel FB, for example oil, is fed at an angle ⁇ relative to the burner axis A.
  • a fuel FB for example oil
  • the fuel supply 13 opens at the mixing tube inner wall in the region of the smallest flow cross-section.
  • at least two, preferably more fuel feeds 13 arranged separately from one another, are to be integrated within the mixing tube 4.
  • the outlet openings of the individual fuel feeds 13 are preferably in a common cross-sectional plane which intersects the burner axis A perpendicular.
  • the fuel supply lines 13 usually open via conventional hole nozzles on the inner wall of the mixing tube 4, but can for optimized fuel feed to produce a very atomized
  • the exemplary embodiment in the lower image representation B1 provides a mixing tube 4 with a straight, hollow-cylindrical inner wall, along which fuel is also discharged into the interior of the mixing tube 4 at an angle ⁇ .
  • the alternative embodiments and arrangements of the fuel feed 13 described for the case A1 can also be used and used.
  • the fuel supply 13 takes place in the region of the mixing tube 4 in each case perpendicular to the burner axis A.
  • the fuel feed 13 also opens in the area of the smallest flow cross section.
  • B2 it is fundamentally irrelevant at which point the fuel supply 13 takes place along the mixing tube, however, for reasons of complete mixing of the fuel fed FB and formation of a homogeneous fuel-air mixture, a central position which is as central as possible or upstream relative to the mixing tube center is advantageous ,
  • the exemplary embodiment according to FIG. 4 provides the fuel supply in the region of the premix burner 1.
  • the fuel supply 13 integrated directly upstream of the transition piece 2 in the sub-cone shells 5 of the premix burner 1.
  • the flame position forming within the combustion chamber can be stabilized.
  • the measure according to the invention makes possible a larger operating range, in particular with burners of a larger design a more optimal distribution of the fuel is possible.
  • the measure according to the invention leads to a reduction of the atomizing or injection pre-pressure for the fuel operation and ensures an improved premixing of the fuel-air mixture.

Abstract

L'invention concerne un brûleur de prémélange doté d'un parcours de mélange (3) destiné à un générateur de chaleur et le mode de fonctionnement de ce brûleur de prémélange. Ce brûleur de prémélange comprend des coques de cône primitif (5) complémentaires qui forment un corps de turbulence, délimitent une chambre de turbulence (6) s'élargissant coniquement et présentent des fentes d'entrée d'air (7) tangentielles. Le long de ces coques, sont réparties des arrivées (8) destinées au combustible gazeux. Ce brûleur de prémélange comprend également au moins une arrivée de combustible (11) placée le long d'un axe de brûleur (A) traversant la chambre de turbulence (6) au centre et destinée au combustible liquide ainsi qu'un tube mélangeur (4) se prolongeant en aval du corps de turbulence par l'intermédiaire d'une pièce de transition (2). L'invention est caractérisée en ce qu'au moins une autre arrivée en combustible (13) destinée au combustible liquide ou gazeux est placée dans la zone du corps de turbulence, de la pièce de transition (2) et/ou du tube mélangeur (4).
EP05804628A 2004-12-23 2005-11-23 Bruleur de premelange dote d'un parcours de melange Withdrawn EP1828684A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH21452004 2004-12-23
PCT/EP2005/056168 WO2006069861A1 (fr) 2004-12-23 2005-11-23 Bruleur de premelange dote d'un parcours de melange

Publications (1)

Publication Number Publication Date
EP1828684A1 true EP1828684A1 (fr) 2007-09-05

Family

ID=34974355

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05804628A Withdrawn EP1828684A1 (fr) 2004-12-23 2005-11-23 Bruleur de premelange dote d'un parcours de melange

Country Status (4)

Country Link
US (1) US8057224B2 (fr)
EP (1) EP1828684A1 (fr)
CN (1) CN101243287B (fr)
WO (1) WO2006069861A1 (fr)

Families Citing this family (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE414874T1 (de) * 2004-01-20 2008-12-15 Alstom Technology Ltd Vormischbrenneranordnung sowie verfahren zum betreiben einer brennkammer
WO2006069861A1 (fr) 2004-12-23 2006-07-06 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange
EP2058590B1 (fr) * 2007-11-09 2016-03-23 Alstom Technology Ltd Procédé de fonctionnement d'un brûleur
EP2225488B1 (fr) 2007-11-27 2013-07-17 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
CN101910723B (zh) * 2007-11-27 2013-07-24 阿尔斯通技术有限公司 用于在预混燃烧器中燃烧氢气的设备
WO2009068427A1 (fr) 2007-11-27 2009-06-04 Alstom Technology Ltd Dispositif et procédé d'utilisation d'une installation de turbine à gaz par recours à un deuxième carburant riche en hydrogène
EP2078898A1 (fr) * 2008-01-11 2009-07-15 Siemens Aktiengesellschaft Brûleur et procédé pour réduire des oscillations de flammes autoinduites
EP2257736B1 (fr) 2008-03-07 2015-11-25 Alstom Technology Ltd Procédé de production de gaz chaud
WO2009109452A1 (fr) 2008-03-07 2009-09-11 Alstom Technology Ltd Ensemble brûleur et son utilisation
EP2260238B1 (fr) * 2008-03-07 2015-12-23 Alstom Technology Ltd Procédé de fonctionnement d'un brûleur à prémélange
EP2107313A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Alimentation étagée de combustible dans un brûleur
EP2208927B1 (fr) * 2009-01-15 2016-03-23 Alstom Technology Ltd Brûleur d'une turbine à gaz
US8667800B2 (en) * 2009-05-13 2014-03-11 Delavan Inc. Flameless combustion systems for gas turbine engines
EP2299178B1 (fr) * 2009-09-17 2015-11-04 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
US20120129111A1 (en) * 2010-05-21 2012-05-24 Fives North America Combustion, Inc. Premix for non-gaseous fuel delivery
ES2462974T3 (es) * 2010-08-16 2014-05-27 Alstom Technology Ltd Quemador de recalentamiento
US20120052451A1 (en) * 2010-08-31 2012-03-01 General Electric Company Fuel nozzle and method for swirl control
US20120144832A1 (en) * 2010-12-10 2012-06-14 General Electric Company Passive air-fuel mixing prechamber
FR2982010B1 (fr) * 2011-10-26 2013-11-08 Snecma Chambre de combustion annulaire dans une turbomachine
US9134023B2 (en) * 2012-01-06 2015-09-15 General Electric Company Combustor and method for distributing fuel in the combustor
EP2650612A1 (fr) * 2012-04-10 2013-10-16 Siemens Aktiengesellschaft Brûleur
JP6231114B2 (ja) * 2012-10-24 2017-11-15 ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ 希釈ガス混合器を備えた２段燃焼
US10065157B2 (en) * 2012-10-26 2018-09-04 Blue Cube Ip Llc Mixer and processes incorporating the same
US9194583B2 (en) * 2013-02-20 2015-11-24 Jorge DE LA SOVERA Mixed fuel vacuum burner-reactor
US9267689B2 (en) * 2013-03-04 2016-02-23 Siemens Aktiengesellschaft Combustor apparatus in a gas turbine engine
US10330320B2 (en) 2013-10-24 2019-06-25 United Technologies Corporation Circumferentially and axially staged annular combustor for gas turbine engine
WO2015061217A1 (fr) 2013-10-24 2015-04-30 United Technologies Corporation Chambre de combustion à gaine étagée de façon circonférentielle et axiale destinée à un moteur à turbine à gaz
CN104110699B (zh) * 2014-07-09 2017-09-15 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机燃烧室的预混合喷嘴
CN104110698B (zh) * 2014-07-09 2017-11-07 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种用于燃气轮机燃烧室的预混合喷嘴
KR102096434B1 (ko) * 2015-07-07 2020-04-02 한화에어로스페이스 주식회사 연소기
CN109073218B (zh) * 2016-03-21 2020-02-28 亚特兰提斯研究实验室公司 焚烧系统
EP3290804A1 (fr) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brûleur avec alimentation d'air et de carburant incorporée dans une paroi du brûleur
CN107062221A (zh) * 2017-05-22 2017-08-18 北京醇能科技有限公司 一种低沸点燃料燃烧器
CN107228826B (zh) * 2017-06-06 2023-09-15 北京金索坤技术开发有限公司 一种用于火焰原子荧光光谱仪的双曲涡旋式传输室
US11555612B2 (en) * 2017-11-29 2023-01-17 Babcock Power Services, Inc. Dual fuel direct ignition burners
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
US10907832B2 (en) 2018-06-08 2021-02-02 General Electric Company Pilot nozzle tips for extended lance of combustor burner
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
FR3099547B1 (fr) * 2019-07-29 2021-10-08 Safran Aircraft Engines Nez d'injecteur de carburant pour turbomachine comprenant une chambre de mise en rotation intérieurement délimitée par un pion
CN110566963A (zh) * 2019-10-14 2019-12-13 康柏森热能科技(苏州)有限公司 一种集成式预混点火枪
CN111520748A (zh) * 2020-03-17 2020-08-11 西北工业大学 一种对冲式预热燃烧室
CN114353121B (zh) * 2022-01-18 2022-12-20 上海交通大学 一种用于燃气轮机的多喷嘴燃料注入方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5375995A (en) * 1993-02-12 1994-12-27 Abb Research Ltd. Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing installation

Family Cites Families (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647568A (en) * 1951-03-30 1953-08-04 Peabody Engineering Corp Burner throat
DE3707773C2 (de) * 1987-03-11 1996-09-05 Bbc Brown Boveri & Cie Einrichtung zur Prozesswärmeerzeugung
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE59209209D1 (de) * 1992-10-16 1998-04-02 Asea Brown Boveri Gasbetriebener Vormischbrenner
DE4316474A1 (de) * 1993-05-17 1994-11-24 Abb Management Ag Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
DE4408256A1 (de) * 1994-03-11 1995-09-14 Abb Management Ag Verfahren und Vorrichtung zur Flammenstabilisation von Vormischbrennern
DE4409918A1 (de) * 1994-03-23 1995-09-28 Abb Management Ag Brenner zum Betrieb einer Brennkammer
DE4426351B4 (de) * 1994-07-25 2006-04-06 Alstom Brennkammer für eine Gasturbine
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
DE4441235A1 (de) * 1994-11-19 1996-05-23 Abb Management Ag Brennkammer mit Mehrstufenverbrennung
DE4444125A1 (de) * 1994-12-12 1996-06-13 Abb Research Ltd Verfahren zur schadstoffarmen Verbrennung
DE4446842B4 (de) * 1994-12-27 2006-08-10 Alstom Verfahren und Vorrichtung zum Zuleiten eines gasförmigen Brennstoffs in einen Vormischbrenner
DE19527453B4 (de) * 1995-07-27 2009-05-07 Alstom Vormischbrenner
DE19545309A1 (de) * 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
DE19608349A1 (de) * 1996-03-05 1997-09-11 Abb Research Ltd Druckzerstäuberdüse
DE19614001A1 (de) * 1996-04-09 1997-10-16 Abb Research Ltd Brennkammer
DE19626240A1 (de) * 1996-06-29 1998-01-02 Abb Research Ltd Vormischbrenner und Verfahren zum Betrieb des Brenners
DE19628960B4 (de) * 1996-07-18 2005-06-02 Alstom Technology Ltd Temperaturmeßvorrichtung
EP0909921B1 (fr) * 1997-10-14 2003-01-02 Alstom Brûleur pour la mise en oeuvre d'un générateur de chaleur
DE59710788D1 (de) * 1997-11-13 2003-10-30 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
DE19757189B4 (de) * 1997-12-22 2008-05-08 Alstom Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
DE59810284D1 (de) * 1998-10-14 2004-01-08 Alstom Switzerland Ltd Brenner für den Betrieb eines Wärmeerzeugers
EP1002992B1 (fr) * 1998-11-18 2004-09-29 ALSTOM Technology Ltd Brûleur
DE19855034A1 (de) * 1998-11-28 2000-05-31 Abb Patent Gmbh Verfahren zum Beschicken eines Brenners für Gasturbinen mit Pilotgas
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
EP1070914B1 (fr) * 1999-07-22 2003-12-03 ALSTOM (Switzerland) Ltd Brûleur à prémélange
DE10040869A1 (de) * 2000-08-21 2002-03-07 Alstom Power Nv Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
DE10056124A1 (de) * 2000-11-13 2002-05-23 Alstom Switzerland Ltd Brennersystem mit gestufter Brennstoff-Eindüsung und Verfahren zum Betrieb
DE10056243A1 (de) * 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
DE10061526A1 (de) * 2000-12-11 2002-06-20 Alstom Switzerland Ltd Vormischbrenneranordnung zum Betrieb einer Brennkammer
DE10061527A1 (de) * 2000-12-11 2002-06-13 Alstom Switzerland Ltd Vormischbrenneranordnung mit katalytischer Verbrennung sowie Verfahren zum Betrieb hierzu
DE10064259B4 (de) 2000-12-22 2012-02-02 Alstom Technology Ltd. Brenner mit hoher Flammenstabilität
DE10104695B4 (de) 2001-02-02 2014-11-20 Alstom Technology Ltd. Vormischbrenner für eine Gasturbine
DE10108560A1 (de) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Verfahren zum Betrieb einer Ringbrennkammer sowie eine diesbezügliche Ringbrennkammer
DE50213936D1 (de) 2001-06-22 2009-12-03 Alstom Technology Ltd Verfahren zum Hochfahren einer Gasturbinenanlage
CN1263983C (zh) * 2001-10-19 2006-07-12 阿尔斯通技术有限公司 用于合成气体的燃烧器
EP1389713A1 (fr) * 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Brûleur pilote annulaire pour sortie de brûleur à prémélange
GB2398375A (en) * 2003-02-14 2004-08-18 Alstom A mixer for two fluids having a venturi shape
EP1510755B1 (fr) * 2003-09-01 2016-09-28 General Electric Technology GmbH Brûleur avec lance et alimentation étagée en carburant
EP1754003B1 (fr) * 2004-06-08 2007-09-19 Alstom Technology Ltd Bruleur a premelange a alimentation etagee en combustible liquide
WO2006069861A1 (fr) 2004-12-23 2006-07-06 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5375995A (en) * 1993-02-12 1994-12-27 Abb Research Ltd. Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing installation

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2006069861A1 *

Also Published As

Publication number Publication date
US20070259296A1 (en) 2007-11-08
CN101243287A (zh) 2008-08-13
US8057224B2 (en) 2011-11-15
CN101243287B (zh) 2013-03-27
WO2006069861A1 (fr) 2006-07-06

Similar Documents

Publication Publication Date Title
EP1828684A1 (fr) Bruleur de premelange dote d'un parcours de melange
EP1802915B1 (fr) Bruleur pour turbine a gaz
DE60007946T2 (de) Eine Brennkammer
EP1807656B1 (fr) Bruleur a premelange
EP0918191B1 (fr) Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP2058590B1 (fr) Procédé de fonctionnement d'un brûleur
EP0902233B1 (fr) Buse de pulvérisation par pression combinée
EP1754003B1 (fr) Bruleur a premelange a alimentation etagee en combustible liquide
EP1356236B1 (fr) Brûleur de prémélange et son mode de fonctionnement
DE10050248A1 (de) Brenner
EP1262714A1 (fr) Brûleur avec recirculation des gaz de combustion
DE19640198A1 (de) Vormischbrenner
WO2008155373A1 (fr) Stabilisation sans rotation de la flamme d'un brûleur à prémélange
EP0503319A2 (fr) Brûleur pour une combustion à mélange préalable d'un combustible liquide et/ou gazeux
EP0777081A2 (fr) Brûleur à prémélange
EP2513562A1 (fr) Brûleur pour une turbine
DE102004049491A1 (de) Vormischbrenner
EP0394800B1 (fr) Brûleur à mélange préalable pour la génération de gaz chaud
EP0481111A1 (fr) Chambre de combustion pour turbine à gaz
EP0816759B1 (fr) Brûleur à prémélange et procédé de mise en oeuvre du brûleur
DE10051221A1 (de) Brenner mit gestufter Brennstoff-Eindüsung
DE19527453B4 (de) Vormischbrenner
EP0742411B1 (fr) Alimentation en air pour une chambre de combustion à prémélange
EP1510755B1 (fr) Brûleur avec lance et alimentation étagée en carburant
DE4445279A1 (de) Einspritzdüse

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20070604

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20091015

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

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

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

Owner name: ANSALDO ENERGIA SWITZERLAND AG

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

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

18D Application deemed to be withdrawn

Effective date: 20180605