EP1999409B1 - Système de brûleur - Google Patents

Système de brûleur Download PDF

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Publication number
EP1999409B1
EP1999409B1 EP07726463.8A EP07726463A EP1999409B1 EP 1999409 B1 EP1999409 B1 EP 1999409B1 EP 07726463 A EP07726463 A EP 07726463A EP 1999409 B1 EP1999409 B1 EP 1999409B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
lance
tip
stage
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.)
Active
Application number
EP07726463.8A
Other languages
German (de)
English (en)
Other versions
EP1999409A1 (fr
Inventor
Adnan Eroglu
Rudolf Lachner
Martin Zajadatz
James Robertson
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 IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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Application filed by Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Publication of EP1999409A1 publication Critical patent/EP1999409A1/fr
Application granted granted Critical
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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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • 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 
    • 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 the field of gas turbines. It relates to a burner assembly according to the preamble of claim 1.
  • FIG. 1 shows a burner assembly 10 in the form of a so-called double-cone burner, which has one of a double cone 11 enclosed swirl space 17 (for the operation of the double-cone burner, see for example the EP-A1-0 321 809 ).
  • a fuel lance 12 projects, from which liquid fuel 16, which is surrounded by shielding air 15, exits in the axial direction at the front end.
  • a premix fuel is injected into the burner in two stages 13 and 14.
  • the premix fuel is discharged from the central fuel lance 12 through a plurality of injection ports (indicated by the arrows in FIG Fig. 1 ) injected radially outwards.
  • the injection ports are formed and arranged to provide a predetermined distribution of the injected premix fuel.
  • the penetration depth of the fuel jets into the intersecting air flow must be sufficiently high.
  • the depth of penetration of a jet in a cross flow depends on the diameter of the jet and on the ratio of the momentum fluxes of jet and cross flow.
  • the object is solved by the entirety of the features of claim 1.
  • the decisive factor for the proposed solution is that in the first stage, the entire premix fuel is injected into the swirl space through two opposite injection openings with an enlarged opening diameter.
  • the injection ports combined in a pair with a large opening diameter enable operation both at idle and at full load with reduced gas pressure.
  • the solution is very simple and robust and can be implemented without difficulty in existing burner arrangements. In addition, fouling by dirt is reduced.
  • the two injection openings of the first stage have a diameter of about 5 mm and the two injection openings are arranged in the circumferential direction by an angle of about 65 degrees twisted out of a median plane, which is oriented parallel to the air flowing tangentially in the double cone.
  • a preferred embodiment of the invention is characterized in that the fuel lance so far protrudes into the swirl space, that the tip of the fuel lance is removed by a distance of 135 mm from the open end of the swirl space, and that the two injection openings in the axial Direction are arranged at a distance of about 115 mm from the top of the fuel lance.
  • liquid fuel can be injected into the swirl space in the axial direction at the tip of the burner lance, wherein the liquid fuel is surrounded by a jacket of shielding air.
  • the burner lance is bounded at the top by an end face perpendicular to the burner axis.
  • the burner lance may be rounded or streamlined at the top.
  • Fig. 2 is in a to Fig. 1 comparable representation of an embodiment of the invention reproduced.
  • the burner assembly 20 comprises a double cone 11, which encloses a swirl space 17, into which a fuel lance 12 projects from the apex of the cone in the axial direction.
  • premix fuel is injected through a plurality of injection openings in the tangent to the swirl chamber 17 air flow.
  • the first stage 18 instead of the many small injection orifices of the prior art, only two opposing injection orifices 19 having a significantly increased diameter are now provided, through which now the entire premix fuel of the first stage 18 is injected. How out Fig.
  • the two injection openings 19 of the first stage 18 are arranged at a distance a away from the tip of the fuel lance 12.
  • the tip of the fuel lance 12 in turn has a distance b from the open end of the swirl space 17.
  • the distance a is 115 mm +/- 10 mm.
  • the distance b is preferably 135 mm.
  • the diameter of the injection openings 19 is 5 mm +/- 0.5 mm.
  • the injection openings 19 are oriented in the radial direction and have relative to the double cone 11 an angular position in the circumferential direction, as is made Fig. 4 becomes clear.
  • a burner arrangement is shown in which the burner lance is delimited at the top by an end face perpendicular to the burner axis (rectangular geometry of the tip).
  • the burner lances are rounded off at the tip or have a streamlined design.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Claims (6)

  1. Dispositif à brûleur (20) avec un corps de tourbillonnement conique disposé de manière concentrique par rapport à un axe de brûleur (21), sous la forme d'un double cône (11), qui entouré un espace de tourbillonnement (17) et avec une lance de carburant (12) centrale se trouvant dans l'axe de brûleur (21), qui dépasse de la pointe du cône du corps de tourbillonnement (11) vers l'espace de tourbillonnement (17), un premier étage (18) étant prévu pour l'introduction de carburant de pré-mélange, dans lequel le carburant de pré-mélange est introduit par des ouvertures d'introduction (19) disposées sur la lance de carburant (12) de manière radiale vers l'extérieur vers l'espace de tourbillonnement (17), et un deuxième étage (14) étant prévu pour l'introduction de carburant de pré-mélange, dans lequel le carburant de pré-mélange est introduit par des ouvertures d'introduction dans le double cône (11) dans un flux d'air guidé dans le double cône (11), moyennant quoi, dans le premier étage (18), l'ensemble du carburant de pré-mélange est introduit par deux ouvertures d'introduction opposées (19) avec un diamètre d'ouverture agrandi dans l'espace de tourbillonnement (17) ; les deux ouvertures d'introduction -19) du premier étage (18) présentant un diamètre d'environ 5 mm ; caractérisé en ce que les deux ouvertures d'introduction (19) sont disposées dans la direction circonférentielle de manière décalée d'un angle (α) d'environ 65 degrés hors d'un plan central (22), qui est orienté parallèlement à l'air entrant de manière tangentielle dans le double cône (11).
  2. Dispositif à brûleur selon la revendication 1, caractérisé en ce que la lance de carburant (12) dépasse dans l'espace de tourbillonnement (17), jusqu'à ce que la pointe de la lance de carburant (12) soit éloignée d'une distance (b) d'environ 135 mm de l'extrémité ouverte de l'espace de tourbillonnement (17) et en ce que les deux ouvertures d'introduction (19) sont disposées dans la direction axiale à une distance (a) d'environ 115 mm de la pointe de la lance de carburant (12).
  3. Dispositif à brûleur selon la revendication 1 ou 2, caractérisé en ce que, au niveau de la pointe de la lance de brûleur (12), un carburant liquide (16) est introduit dans la direction axiale dans l'espace de tourbillonnement (17).
  4. Dispositif à brûleur selon la revendication 3, caractérisé en ce que le carburant liquide (16) est entouré d'une enveloppe d'air de protection (15).
  5. Dispositif à brûleur selon l'une des revendications 1 à 4, caractérisé en ce que la lance de brûleur (12) est limitée, au niveau de la pointe, par une face frontale perpendiculaire à l'axe du brûleur (21).
  6. Dispositif à brûleur selon l'une des revendications 1 à 4, caractérisé en ce que la lance de brûleur (12) présente, au niveau de la pointe, une forme arrondie ou une forme aérodynamique.
EP07726463.8A 2006-03-30 2007-02-22 Système de brûleur Active EP1999409B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH5322006 2006-03-30
PCT/EP2007/051705 WO2007113054A1 (fr) 2006-03-30 2007-02-22 Système de brûleur

Publications (2)

Publication Number Publication Date
EP1999409A1 EP1999409A1 (fr) 2008-12-10
EP1999409B1 true EP1999409B1 (fr) 2018-05-02

Family

ID=36989348

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07726463.8A Active EP1999409B1 (fr) 2006-03-30 2007-02-22 Système de brûleur

Country Status (5)

Country Link
US (1) US8801429B2 (fr)
EP (1) EP1999409B1 (fr)
JP (1) JP2009531641A (fr)
AU (1) AU2007233890B2 (fr)
WO (1) WO2007113054A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2348256A1 (fr) * 2010-01-26 2011-07-27 Alstom Technology Ltd Procédé de fonctionnement d'une turbine à gaz et turbine à gaz
CH703655A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Vormischbrenner für eine gasturbine.
US10571135B2 (en) 2012-04-09 2020-02-25 David Kreutzman Renewable energy hot water heater with heat pump
CN105650622B (zh) * 2016-03-25 2018-05-18 宿元凯 一种烹制中餐用环保节能金黄色火焰燃烧器
US10760793B2 (en) * 2017-07-21 2020-09-01 General Electric Company Jet in cross flow fuel nozzle for a gas turbine engine
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618928A (en) * 1944-05-19 1952-11-25 Power Jets Res & Dev Ltd Combustion apparatus with vaned fuel injector means
GB2175684B (en) * 1985-04-26 1989-12-28 Nippon Kokan Kk Burner
CH672541A5 (fr) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
DE3737247C1 (de) * 1987-11-03 1989-03-02 Zettner Michael L Brenneinrichtung
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE59000422D1 (de) * 1989-04-20 1992-12-10 Asea Brown Boveri Brennkammeranordnung.
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
US5461865A (en) * 1994-02-24 1995-10-31 United Technologies Corporation Tangential entry fuel nozzle
JP4625609B2 (ja) * 2000-06-15 2011-02-02 アルストム テクノロジー リミテッド バーナーの運転方法と段階的予混合ガス噴射バーナー
DE10031264A1 (de) * 2000-06-27 2002-01-17 Bosch Gmbh Robert Kraftstoffeinspritzventil für Brennkraftmaschinen
DE10205839B4 (de) * 2002-02-13 2011-08-11 Alstom Technology Ltd. Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
EP1504222B1 (fr) * 2002-05-16 2007-07-11 Alstom Technology Ltd Bruleur a premelange

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
AU2007233890B2 (en) 2010-07-01
JP2009531641A (ja) 2009-09-03
WO2007113054A1 (fr) 2007-10-11
AU2007233890A1 (en) 2007-10-11
US20090068609A1 (en) 2009-03-12
US8801429B2 (en) 2014-08-12
EP1999409A1 (fr) 2008-12-10

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