EP0210462A1 - Chambre de combustion double - Google Patents

Chambre de combustion double Download PDF

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Publication number
EP0210462A1
EP0210462A1 EP86109039A EP86109039A EP0210462A1 EP 0210462 A1 EP0210462 A1 EP 0210462A1 EP 86109039 A EP86109039 A EP 86109039A EP 86109039 A EP86109039 A EP 86109039A EP 0210462 A1 EP0210462 A1 EP 0210462A1
Authority
EP
European Patent Office
Prior art keywords
fuel
dual burner
cone
swirl body
dual
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
EP86109039A
Other languages
German (de)
English (en)
Other versions
EP0210462B1 (fr
Inventor
Jean Dr. Hellat
Jakob Dr. Keller
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG 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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0210462A1 publication Critical patent/EP0210462A1/fr
Application granted granted Critical
Publication of EP0210462B1 publication Critical patent/EP0210462B1/fr
Expired 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 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
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • 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
    • F23R3/36—Supply of different fuels
    • 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 dual burner according to the preamble of claim 1. It also relates to a method for mixing air with the liquid fuel flowing into the dual burner.
  • a known possibility of building a detachable swirl body is to provide a tubular jacket with tangential entry slots. This creates a potential vortex that flows axially.
  • vortex breakdown zones in a potential vortex have very poor stability properties.
  • the invention seeks to remedy this.
  • the object of the invention is to produce a stable vortex backflow zone in a dual burner of the type mentioned at the outset.
  • the conditions must be met, according to which the axial profile of the vortex flow generated by the swirl body has a speed increase in the vicinity of the axis, while the swirl must decrease sharply towards the axis.
  • the objectives of the invention are basically achieved in that slotted cones are provided with suitable opening angles; this gives you an optimal opportunity to combine the advantages of a potential vortex tube and a fluid-mechanically perfect swirl body.
  • a vortex flow is obtained which is low in swirl in the center and has an axial speed excess. Because the number of swirls of this burner increases strongly in the axial direction and reaches the breakdown value or the critical value at the end of the burner, this results in a positionally stable vortex backflow zone.
  • Fig. 1 shows a dual burner in the direction of flow to the media used there.
  • the dual burner which is placed in front of the combustion chamber 13 of a combustion chamber, which is only hinted at, is essentially composed of a structure formed into a swirl body, an oil line 2 and a gas line 3.
  • the swirl body structure itself consists of two double-curved plates which are produced by bending flat plates can be.
  • the sheets are folded on a certain diagonal and stiffened with a rib (see FIGS. 2, 3, 4). Because the diagonals diverge in a cone-shaped manner in the central plane of the flow direction, an arrangement of inner cones 4b, 5b that expand in the flow direction and an arrangement of outer cones 4a, 5a that taper in the flow direction are created.
  • the fuels introduced - fuel gas and fuel oil - are introduced individually into the swirl body 1 and thus meet the requirements placed on a dual burner.
  • the oil line 2 divides in front of the swirl body 1 into two oil nozzles 2a, 2b in such a way that their injection is directed axially onto the outer cone 4a, 5a.
  • the impulse of the oil injection at full load is selected so that the oil film 6 penetrates to the end of an outer cone 4a or 5a.
  • the penetration depth decreases accordingly, so that the outer areas of the vortex flow remain free of fuel. This results in self-regulation, which means that the fuel / air mixture 7a in the vortex center never becomes too lean or too rich.
  • the swirl strength of the vortex flow is dependent on the selected width of the slot that results between the outer cone 4a, 5a and the inner cone 4b, 5b.
  • the outer cones 4a, 5a tapering in the direction of flow thus fulfill various functions. On the one hand, they serve as carriers of the oil film 6 released by the oil nozzles 2a, 2b; Furthermore, the outer cones 4a, 5a serve to guide the flow of the working mixture, which rolls in the axial direction due to the swirl movement.
  • the radiant heat which the sheets receive from the combustion chamber 13 can be partially transferred to the oil film 6 here.
  • the supplied air 7 finds at least partially evaporated Del, as a result of which the mixing takes place optimally.
  • the inner cones 4b, 5b which widen in the direction of flow, have fuel lines 8 on the bend end, as a continuation of the gas line 3, which serve to supply a gaseous fuel.
  • the slot widths 14 which cannot be seen in FIG.
  • the backflow zone 12 begins at the downstream end of the inner cones 4b, 5b.
  • the backflow zone 12 is inherently positionally stable.
  • the taper and expansion rates of the cones 4a, 4b and. 4b, 5b depend on the properties of the combustion chamber, as does the overall length of the swirl body 1.
  • FIG. 2 3, 4 are views through the planes II, III, IV according to FIG. 1. This clearly shows how the cones 4a, 5a and 4b, 5b taper respectively. expand.
  • the plates 4, 5 are folded in the planes of the diagonals 10a, 10b and each stiffened with a rib 10.
  • These figures also clearly show how the air 7 flows tangentially into the cone and how the swirl movement is initiated by its curvature.
  • the portions of the oil film 6 which do not evaporate immediately are "rolled up" in layers by the swirled air 7, which ensures that the fuel / air mixture has a homogeneous concentration.
  • the slot widths 14 between the inner and outer cones increase, while the inflow openings 14a between fuel lines 8 and outer cones 4a, 5b decrease.
  • the fuel lines 8 are provided with fuel nozzles 9 which inject the fuel gas towards the center of the swirl body 1.
  • the tangentially flowing air 7 is thus homogeneously enriched with the available fuel gas.
  • the fuel is "rolled in” by the tangentially flowing air 7 between relatively thin layers of air, as a result of which subsequent mixing is unnecessary.
  • the swirl body 1 is closed on the combustion chamber side, as can be seen in FIG. 4, with the perforated plate 11, through which, as already explained, cooling air or dilution air can reach the combustion chamber 13.
  • FIG. 5 shows an expanded variant of the swirl body 1 already shown in FIG. 1.
  • the local version is supplemented with a pilot burner 15.
  • the gas line 3 is extended in the flow direction via the fuel lines 8.
  • the pilot burner version is particularly suitable if the swirl body 1 has more than two pairs of cones.
  • FIGS. 6, 7, 8, 9 - which views can be seen through the planes VI, VII, VIII, IX according to FIG. 5 - the swirl body 1 constructed here from four pairs of cones does not differ conceptually from the one already explained , variant consisting of two pairs of cones.
  • the mixing of the fuels with the tangentially flowing air 7 is easier here, however, because it has to "roll in” smaller fuel rates.
  • the injection of the fuel via the four oil nozzles 2a, 2b, 2c, 2d is also directed axially onto the outer cones 4a, 5a, 16a, 17a.
  • the swirl body 1 now consists of four double-curved sheets 4, 5, 16, 17, which are in the planes of the diagonals 10a, 10b, 10c, 10d are folded into double cones. These diagonals run outwards in the direction of flow in a cone-shaped manner, so that the outer cones 4a, 5a, 16a, 17a taper, while the inner cones 4b, 5b, 16b, 17b expand.
  • the inner cones 4b, 5b, 16b, 17b each carry at the end a fuel line 8 provided with fuel nozzles 9, which in cooperation with the rib 10 serves to increase the rigidity of the folded sheets 4, 5, 16, 17.
EP86109039A 1985-07-30 1986-07-02 Chambre de combustion double Expired EP0210462B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3289/85 1985-07-30
CH328985 1985-07-30

Publications (2)

Publication Number Publication Date
EP0210462A1 true EP0210462A1 (fr) 1987-02-04
EP0210462B1 EP0210462B1 (fr) 1989-03-15

Family

ID=4252764

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86109039A Expired EP0210462B1 (fr) 1985-07-30 1986-07-02 Chambre de combustion double

Country Status (6)

Country Link
US (1) US4781030A (fr)
EP (1) EP0210462B1 (fr)
JP (1) JPH06103085B2 (fr)
CA (1) CA1286886C (fr)
DE (1) DE3662462D1 (fr)
IN (1) IN167458B (fr)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809A1 (fr) * 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
EP0387532A1 (fr) * 1989-03-15 1990-09-19 Asea Brown Boveri Ag Chambre de combustion d'une turbine à gaz
EP0394911A1 (fr) * 1989-04-27 1990-10-31 Asea Brown Boveri Ag Installation de combustion
EP0394800A1 (fr) * 1989-04-24 1990-10-31 Asea Brown Boveri Ag Brûleur à mélange préalable pour la génération de gaz chaud
EP0401529A1 (fr) * 1989-06-06 1990-12-12 Asea Brown Boveri Ag Chambre de combustion d'une turbine à gaz
US5044935A (en) * 1989-03-15 1991-09-03 Asea Brown Boveri Ltd. Method and apparatus for operating a firing plant using fossil fuels
EP0481111A1 (fr) * 1990-10-17 1992-04-22 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
US5147200A (en) * 1989-12-01 1992-09-15 Asea Brown Boveri, Ltd. Method of operating a firing installation
EP0521325A1 (fr) * 1991-07-03 1993-01-07 Asea Brown Boveri Ag Chambre de combustion
US5193995A (en) * 1987-12-21 1993-03-16 Asea Brown Boveri Ltd. Apparatus for premixing-type combustion of liquid fuel
EP0592717A1 (fr) * 1992-10-16 1994-04-20 Asea Brown Boveri Ag Brûleur opérant au gaz du type à prémélange
EP0593816A1 (fr) * 1992-10-23 1994-04-27 Asea Brown Boveri Ag Brûleur avec dispositif d'allumage électrique
WO1995023316A1 (fr) * 1994-02-24 1995-08-31 United Technologies Corporation Buse d'injection de carburant a entree tangentielle
DE4435473A1 (de) * 1994-10-04 1996-04-11 Abb Management Ag Vormischbrenner für flüssigen Brennstoff
DE4440558A1 (de) * 1994-11-12 1996-05-15 Abb Research Ltd Vormischbrenner
EP0786626A1 (fr) * 1995-12-27 1997-07-30 Asea Brown Boveri Ag Brûleur à prémélange
EP0694730A3 (fr) * 1994-07-25 1998-05-06 Abb Research Ltd. Bruleur
EP1262714A1 (fr) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
DE19515082B4 (de) * 1995-04-25 2005-02-03 Alstom Vormischbrenner
DE102004015904A1 (de) * 2004-03-31 2005-10-20 Alstom Technology Ltd Baden Verfahren zur Flüssigbrennstoffzerstäubung in einem Vormischbrenner sowie Vormischbrenner
US7065971B2 (en) 2003-03-05 2006-06-27 Alstom Technology Ltd. Device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
US7428817B2 (en) 2004-02-12 2008-09-30 Alstom Technology Ltd Premix burner with a swirl generator delimiting a conical swirl space and having sensor monitoring
US7632091B2 (en) 2005-03-09 2009-12-15 Alstom Technology Ltd. Premix burner for operating a combustion chamber
US7896646B2 (en) 2004-01-20 2011-03-01 Alstom Technology Ltd Premixing burner arrangement for operating a combustion chamber in addition to a method for operating a combustion chamber
US8007273B2 (en) 2005-03-09 2011-08-30 Alstom Technology Ltd. Premixing burner for generating an ignitable fuel/air mixture
DE102005011287B4 (de) 2004-03-31 2018-07-19 Ansaldo Energia Ip Uk Limited Verfahren sowie eine Vorrichtung zum Betreiben wenigstens eines Brenners zur Befeuerung der Brennkammer einer Wärmekraftmaschine oder Gasturbine

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CH680467A5 (fr) * 1989-12-22 1992-08-31 Asea Brown Boveri
US5307634A (en) * 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle
SE9304194L (sv) * 1993-12-17 1995-06-18 Abb Stal Ab Bränslespridare
DE4424639A1 (de) * 1994-07-13 1996-01-18 Abb Research Ltd Verfahren und Vorrichtung zur Brennstoffverteilung in einem sowohl für flüssige als auch für gasförmige Brennstoffe geeigneten Brenner
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle
DE4441235A1 (de) * 1994-11-19 1996-05-23 Abb Management Ag Brennkammer mit Mehrstufenverbrennung
DE4446842B4 (de) * 1994-12-27 2006-08-10 Alstom Verfahren und Vorrichtung zum Zuleiten eines gasförmigen Brennstoffs in einen Vormischbrenner
DE19502796B4 (de) * 1995-01-30 2004-10-28 Alstom Brenner
EP0807213B1 (fr) * 1995-02-03 2002-07-31 Rolls-Royce Deutschland Ltd & Co KG Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz
DE19512645A1 (de) * 1995-04-05 1996-10-10 Bmw Rolls Royce Gmbh Vorrichtung zur Kraftstoffaufbereitung für eine Brennkammer
DE19545309A1 (de) * 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
DE19547914A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Vormischbrenner für einen Wärmeerzeuger
DE19619873A1 (de) * 1996-05-17 1997-11-20 Abb Research Ltd Brenner
DE19626240A1 (de) * 1996-06-29 1998-01-02 Abb Research Ltd Vormischbrenner und Verfahren zum Betrieb des Brenners
DE19654008B4 (de) * 1996-12-21 2006-08-10 Alstom Brenner
DE19721937B4 (de) * 1997-05-26 2008-12-11 Alstom Vormischbrenner zum Betrieb eines Aggregates zur Erzeugung eines Heissgases
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
US6141954A (en) * 1998-05-18 2000-11-07 United Technologies Corporation Premixing fuel injector with improved flame disgorgement capacity
GB0219461D0 (en) * 2002-08-21 2002-09-25 Rolls Royce Plc Fuel injection arrangement
EP1601913A1 (fr) * 2003-03-07 2005-12-07 Alstom Technology Ltd Bruleur de premelange
US20060283181A1 (en) * 2005-06-15 2006-12-21 Arvin Technologies, Inc. Swirl-stabilized burner for thermal management of exhaust system and associated method
EP2116766B1 (fr) * 2008-05-09 2016-01-27 Alstom Technology Ltd Brûleur avec lance à combustible
JP5462527B2 (ja) * 2009-05-19 2014-04-02 大阪瓦斯株式会社 管状火炎バーナ
EP2685160B1 (fr) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685161B1 (fr) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Agencement de chambre de combustion, en particulier pour turbine à gaz
JP2013228207A (ja) * 2013-08-15 2013-11-07 Osaka Gas Co Ltd 管状火炎バーナ
JP6190670B2 (ja) * 2013-08-30 2017-08-30 三菱日立パワーシステムズ株式会社 ガスタービン燃焼システム
JP6123720B2 (ja) * 2014-03-26 2017-05-10 Ｊｆｅスチール株式会社 多管式管状火炎バーナ
CN108224473A (zh) * 2017-12-28 2018-06-29 中国航发四川燃气涡轮研究院 一种突扩内锥火焰稳定结构的一体化加力燃烧室

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GB675092A (en) * 1949-01-25 1952-07-02 Rolls Royce Improvements relating to combustion systems of gas-turbine engines
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Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4932861A (en) * 1987-12-21 1990-06-12 Bbc Brown Boveri Ag Process for premixing-type combustion of liquid fuel
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
EP0321809A1 (fr) * 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
US5193995A (en) * 1987-12-21 1993-03-16 Asea Brown Boveri Ltd. Apparatus for premixing-type combustion of liquid fuel
EP0387532A1 (fr) * 1989-03-15 1990-09-19 Asea Brown Boveri Ag Chambre de combustion d'une turbine à gaz
US5044935A (en) * 1989-03-15 1991-09-03 Asea Brown Boveri Ltd. Method and apparatus for operating a firing plant using fossil fuels
CH678757A5 (fr) * 1989-03-15 1991-10-31 Asea Brown Boveri
US5081844A (en) * 1989-03-15 1992-01-21 Asea Brown Boveri Ltd. Combustion chamber of a gas turbine
US5127821A (en) * 1989-04-24 1992-07-07 Asea Brown Boveri Ltd. Premixing burner for producing hot gas
EP0394800A1 (fr) * 1989-04-24 1990-10-31 Asea Brown Boveri Ag Brûleur à mélange préalable pour la génération de gaz chaud
CH679692A5 (fr) * 1989-04-24 1992-03-31 Asea Brown Boveri
US5118283A (en) * 1989-04-27 1992-06-02 Asea Brown Boveri Ltd. Combustion installation
CH680816A5 (fr) * 1989-04-27 1992-11-13 Asea Brown Boveri
EP0394911A1 (fr) * 1989-04-27 1990-10-31 Asea Brown Boveri Ag Installation de combustion
CH680084A5 (fr) * 1989-06-06 1992-06-15 Asea Brown Boveri
EP0401529A1 (fr) * 1989-06-06 1990-12-12 Asea Brown Boveri Ag Chambre de combustion d'une turbine à gaz
US5147200A (en) * 1989-12-01 1992-09-15 Asea Brown Boveri, Ltd. Method of operating a firing installation
EP0481111A1 (fr) * 1990-10-17 1992-04-22 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
US5274993A (en) * 1990-10-17 1994-01-04 Asea Brown Boveri Ltd. Combustion chamber of a gas turbine including pilot burners having precombustion chambers
EP0521325A1 (fr) * 1991-07-03 1993-01-07 Asea Brown Boveri Ag Chambre de combustion
US5249955A (en) * 1991-07-03 1993-10-05 Asea Brown Boveri Ltd. Burner and ignitor arrangement
CH684962A5 (de) * 1991-07-03 1995-02-15 Asea Brown Boveri Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder einer Feuerungsanlage.
US5482457A (en) * 1992-10-16 1996-01-09 Asea Brown Boveri Ltd. Gas-operated premixing burner
EP0592717A1 (fr) * 1992-10-16 1994-04-20 Asea Brown Boveri Ag Brûleur opérant au gaz du type à prémélange
EP0593816A1 (fr) * 1992-10-23 1994-04-27 Asea Brown Boveri Ag Brûleur avec dispositif d'allumage électrique
US5413478A (en) * 1992-10-23 1995-05-09 Asea Brown Boveri Ltd. Burner with an electric ignition device
WO1995023316A1 (fr) * 1994-02-24 1995-08-31 United Technologies Corporation Buse d'injection de carburant a entree tangentielle
EP0694730A3 (fr) * 1994-07-25 1998-05-06 Abb Research Ltd. Bruleur
DE4435473A1 (de) * 1994-10-04 1996-04-11 Abb Management Ag Vormischbrenner für flüssigen Brennstoff
DE4440558A1 (de) * 1994-11-12 1996-05-15 Abb Research Ltd Vormischbrenner
EP0711953A2 (fr) * 1994-11-12 1996-05-15 Abb Research Ltd. Brûleur à prémélange
EP0711953A3 (fr) * 1994-11-12 1997-09-03 Abb Research Ltd Brûleur à prémélange
DE19515082B4 (de) * 1995-04-25 2005-02-03 Alstom Vormischbrenner
EP0786626A1 (fr) * 1995-12-27 1997-07-30 Asea Brown Boveri Ag Brûleur à prémélange
EP1262714A1 (fr) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
US6672863B2 (en) 2001-06-01 2004-01-06 Alstom Technology Ltd Burner with exhaust gas recirculation
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
US7065971B2 (en) 2003-03-05 2006-06-27 Alstom Technology Ltd. Device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations
US7896646B2 (en) 2004-01-20 2011-03-01 Alstom Technology Ltd Premixing burner arrangement for operating a combustion chamber in addition to a method for operating a combustion chamber
US7428817B2 (en) 2004-02-12 2008-09-30 Alstom Technology Ltd Premix burner with a swirl generator delimiting a conical swirl space and having sensor monitoring
DE102004015904A1 (de) * 2004-03-31 2005-10-20 Alstom Technology Ltd Baden Verfahren zur Flüssigbrennstoffzerstäubung in einem Vormischbrenner sowie Vormischbrenner
DE102005011287B4 (de) 2004-03-31 2018-07-19 Ansaldo Energia Ip Uk Limited Verfahren sowie eine Vorrichtung zum Betreiben wenigstens eines Brenners zur Befeuerung der Brennkammer einer Wärmekraftmaschine oder Gasturbine
US7632091B2 (en) 2005-03-09 2009-12-15 Alstom Technology Ltd. Premix burner for operating a combustion chamber
US8007273B2 (en) 2005-03-09 2011-08-30 Alstom Technology Ltd. Premixing burner for generating an ignitable fuel/air mixture

Also Published As

Publication number Publication date
EP0210462B1 (fr) 1989-03-15
JPH06103085B2 (ja) 1994-12-14
JPS6338812A (ja) 1988-02-19
IN167458B (fr) 1990-10-27
US4781030A (en) 1988-11-01
CA1286886C (fr) 1991-07-30
DE3662462D1 (en) 1989-04-20

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