EP3250857B1 - Agencement de brûleur - Google Patents

Agencement de brûleur Download PDF

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Publication number
EP3250857B1
EP3250857B1 EP16713412.1A EP16713412A EP3250857B1 EP 3250857 B1 EP3250857 B1 EP 3250857B1 EP 16713412 A EP16713412 A EP 16713412A EP 3250857 B1 EP3250857 B1 EP 3250857B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
arrangement
air passage
annular
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
EP16713412.1A
Other languages
German (de)
English (en)
Other versions
EP3250857A1 (fr
Inventor
Andreas Böttcher
Tobias Krieger
Patrick Lapp
Andreas Mann
Simon Purschke
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.)
Siemens AG
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Siemens AG
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Publication date
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Publication of EP3250857A1 publication Critical patent/EP3250857A1/fr
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Publication of EP3250857B1 publication Critical patent/EP3250857B1/fr
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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
    • F23R3/02—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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/70—Baffles or like flow-disturbing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D3/00—Burners using capillary action
    • F23D3/02—Wick burners
    • F23D3/18—Details of wick burners
    • F23D3/28—Wick-adjusting devices
    • F23D3/34—Wick stop devices; Wick-fixing 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
    • F23R3/02—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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air

Definitions

  • the invention relates to a burner arrangement for a combustion chamber, in particular a gas turbine combustion chamber, for burning fluid fuels.
  • a second premixed fuel stage can be integrated into the pilot burner. This stage must then also be supplied via its own fuel supply and fuel channel.
  • the invention solves this problem in that, in the case of such a burner arrangement for a combustion chamber, in particular a gas turbine combustion chamber, for firing fluidic fuels, with a main burner and one arranged centrally therein Pilot burner, which is used to ignite and / or to stabilize the combustion of the main burner, the main burner comprising a first ring air duct for supplying combustion air and first fuel nozzles for injecting fuel into the first ring air duct, the pilot burner comprising a second ring air duct for supplying combustion air and one Burner head with second fuel nozzles for injecting a fuel into the second ring air duct, the second fuel nozzles being provided as separately controllable first and second fuel stages, for supplying fuel to the first and second fuel stages, a burner carrier tube connected to the burner head with a tube wall, the Pipe wall has at least a first and a second deep hole running parallel to the longitudinal axis of the burner support tube for supplying the first and second fuel stages with fuel.
  • the first and second deep-hole bores are expediently arranged on different radii in relation to the longitudinal axis of the burner support tube in the tube wall, so that fuel can be fed directly to a respective fuel stage via straight bores.
  • the production of such bores is comparatively inexpensive.
  • the burner carrier tube has a diffusion gas passage on its axis, which also opens into the burner head, so that diffusion operation is also possible.
  • the burner support tube is connected to a support plate in the flow direction of a fuel upstream of the burner head, the support plate having fuel ring distributors, from which the at least one first and a second deep-hole bore branch off.
  • the carrier plate has fuel connections which open into the fuel ring distributor.
  • the second ring air duct which advantageously has second swirl vanes, the second fuel nozzles being arranged in the second swirl vanes.
  • the Figure 1 shows schematically and by way of example a section through part of a burner arrangement 1 according to the invention.
  • the burner arrangement 1 is essentially radially symmetrical about the longitudinal axis 13 and comprises a main burner 2 and a pilot burner 3 arranged therein, which serves to ignite and / or stabilize the combustion of the main burner 2.
  • the second fuel nozzles 8 are provided as first and second fuel stages 9, 10, each fuel stage 9, 10 having its own fuel supply.
  • Figure 3 shows a downstream detail of the pilot burner 3 Figure 2 , in particular the pilot burner head 7 with the fuel supply for the first and second fuel stages 9, 10.
  • Figure 4 shows an upstream detail of the pilot burner 3 Figure 2 , in particular the compensator 37 of the tube-in-tube construction.
  • the pilot burner 3 according to the invention is shown in different sectional planes.
  • the section runs through second deep-hole bores 15, which represent the inner channel 38
  • in FIG Figure 6 is the corresponding view with first deep hole 14 for the outer channel 39.
  • the first and second deep hole 14, 15 are arranged on different radii 16, 17 in relation to the longitudinal axis 13 of the burner support tube 11 in the tube wall 12.
  • the at least one first and a second deep hole 14, 15 each open into a fuel distribution channel 18, 19 of a fuel stage 9, 10.
  • Figure 7 shows a side view of the downstream end of the burner support tube 11 of the burner arrangement 1.
  • the ends of the first and second deep hole bores 14, 15 of the inner and outer channels 38, 39 can be seen.
  • Figure 8 a section through the support plate 21 with the first and second fuel ring manifold 22, 23 and the outer channel 39 formed by deep hole bores 14 in the tube wall 12 of the burner support tube 11th
  • the Figure 9 shows a section through the carrier plate 21 with the first and second fuel ring distributors 22, 23 and the inner channel 38 formed by deep-hole bores 15 in the tube wall 12 of the burner carrier tube 11
  • Figure 9 a section through the serious fuel connection 24 to the first fuel ring distributor 22 for the outer channel 39.
  • the Figure 10 finally shows a section through the carrier plate 21 with the second fuel connection 25 to the second fuel ring distributor 23 for the inner channel 38
  • Figure 10 recognizable that the second fuel ring distributor 23 for the inner channel 38 is comparatively close below the surface of the carrier plate 21.
  • the fuel connection 25 is implemented via a screw connector 26 with a through bore 27 and essentially radial openings 28 in the external thread 29.
  • the Figures 11 and 12 show such a screw connector 26 in plan view and in section.
  • FIG Figure 13 shows a detailed view of the burner head 7 with transition to the burner support tube 11.
  • the burner head 7, which in the Figure 14 shown in the oblique view is the same as in FIG Figure 3 , According to the invention, only the burner support tube 11 is changed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Claims (9)

  1. Agencement (1) de brûleur d'une chambre de combustion, notamment d'une chambre de combustion de turbine à gaz, pour brûler des combustibles fluides, comprenant un brûleur (2) principal et un brûleur (3) pilote, qui y est disposé centralement et qui sert à amorcer et/ou à stabiliser la combustion du bruleur (2) principal, le brûleur (2) principal comprenant un premier conduit (4) annulaire pour de l'air, pour apporter de l'air de combustion, et une première buse (5) à combustible pour injecter un combustible dans le premier conduit (4) annulaire pour de l'air, le brûleur (3) pilote comprenant un deuxième conduit (6) annulaire pour de l'air, pour apporter de l'air de combustion, et une tête (7) de brûleur ayant des deuxièmes buses (8) à combustible pour injecter un combustible dans le deuxième conduit (6) annulaire pour de l'air, les deuxièmes buses (8) à combustible étant prévues sous la forme de premier et deuxième étages (9, 10) de combustible, pouvant être commandés séparément, caractérisé en ce que, pour apporter du combustible au premier et au deuxième étages (9, 10) de combustible, est prévu un tuyau (11) de support de brûleur, qui se raccorde à la tête (7) du brûleur et qui a une paroi (12) tubulaire, et en ce que la paroi (12) tubulaire a, parallèlement à l'axe (13) longitudinal du tuyau (11) de support de brûleur, au moins un premier et un deuxième trous (14, 15) traversants profonds pour l'alimentation en combustible des premier et deuxième étages (9, 10) de combustible.
  2. Agencement (1) de brûleur suivant la revendication 1, dans lequel le premier et le deuxième trous (14, 15) traversants profonds sont disposés dans la paroi (12) tubulaire sur des rayons (16, 17) différents rapportés à l'axe (13) longitudinal du tuyau (11) de support de brûleur.
  3. Agencement (1) suivant l'une des revendications précédentes, dans lequel le au moins un premier et un deuxième trous (14, 15) traversants profonds débouchent dans, respectivement, un conduit (18, 19) de répartition de combustible d'un étage (9, 10) de combustible.
  4. Agencement (1) suivant l'une des revendications précédentes, dans lequel le tuyau (11) de support de brûleur a, sur son axe (13), un passage (20) de gaz de diffusion, qui débouche également dans la tête (7) du brûleur.
  5. Agencement (1) suivant l'une des revendications précédentes, dans lequel le tuyau (11) de support de brûleur communique, dans le sens d'écoulement d'un combustible, en amont de la tête (7) du brûleur, avec un plateau (21) de support, le plateau 21) de support ayant des répartiteurs (22, 23) annulaires de combustible, desquels bifurquent le au moins un premier et un deuxième trous (14, 15) traversants profonds.
  6. Agencement (1) suivant la revendication 5, dans lequel le plateau (21) de support a des raccords (24, 25) de combustible, qui débouchent dans les répartiteurs (22, 23) annulaires de combustible.
  7. Agencement (1) suivant la revendication 6, dans lequel un raccord (25) de combustible est produit par l'intermédiaire d'un connecteur (26) vissé à alésage (27) traversant et à ouvertures (28) sensiblement radiales dans le filetage (29) extérieur, les ouvertures (28) radiales venant, à l'état vissé, au niveau d'un répartiteur (23) annulaire de combustible.
  8. Agencement (1) suivant l'une des revendications précédentes, dans lequel le premier conduit (4) annulaire pour de l'air a de premières pales (30) de tourbillonnement et les premières buses à combustible sont montées dans les premières pales (30) de tourbillonnement.
  9. Agencement (1) suivant l'une des revendications précédentes, dans lequel le deuxième conduit (6) annulaire pour de l'air a des deuxièmes pales (31) de tourbillonnement et les deuxièmes buses (8) à combustible sont montées dans les deuxièmes pales (31) de tourbillonnement.
EP16713412.1A 2015-04-08 2016-03-30 Agencement de brûleur Active EP3250857B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015206227.9A DE102015206227A1 (de) 2015-04-08 2015-04-08 Brenneranordnung
PCT/EP2016/056892 WO2016162248A1 (fr) 2015-04-08 2016-03-30 Ensemble brûleur

Publications (2)

Publication Number Publication Date
EP3250857A1 EP3250857A1 (fr) 2017-12-06
EP3250857B1 true EP3250857B1 (fr) 2020-01-01

Family

ID=55646580

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16713412.1A Active EP3250857B1 (fr) 2015-04-08 2016-03-30 Agencement de brûleur

Country Status (5)

Country Link
EP (1) EP3250857B1 (fr)
CN (1) CN107429918B (fr)
DE (1) DE102015206227A1 (fr)
RU (1) RU2669439C1 (fr)
WO (1) WO2016162248A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111720732B (zh) * 2020-05-28 2022-05-13 克莱普（浙江）气体设备有限公司 全自动燃料加热整体式气化器
CN112283706B (zh) * 2020-11-20 2024-05-14 华侨大学 一种多枪旋流式低氮燃烧器

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010061626A1 (de) * 2010-01-05 2011-07-07 General Electric Company, N.Y. Brennstoffzuführsysteme für Sekundärverbrennung

Family Cites Families (13)

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Publication number Priority date Publication date Assignee Title
DE59204270D1 (de) * 1991-04-25 1995-12-14 Siemens Ag Brenneranordnung, insbesondere für gasturbinen, zur schadstoffarmen verbrennung von kohlegas und anderen brennstoffen.
US6698207B1 (en) * 2002-09-11 2004-03-02 Siemens Westinghouse Power Corporation Flame-holding, single-mode nozzle assembly with tip cooling
EP1659339A1 (fr) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Procédé de démarrage d'un brûleur
FR2881813B1 (fr) * 2005-02-09 2011-04-08 Snecma Moteurs Carenage de chambre de combustion de turbomachine
US8448441B2 (en) * 2007-07-26 2013-05-28 General Electric Company Fuel nozzle assembly for a gas turbine engine
DE102009038848A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brenner, insbesondere für Gasturbinen
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
IT1397215B1 (it) * 2009-12-29 2013-01-04 Ansaldo Energia Spa Assieme bruciatore per un impianto a turbina a gas e impianto a turbina a gas comprendente detto assieme bruciatore
EP2503240A1 (fr) * 2011-03-22 2012-09-26 Siemens Aktiengesellschaft Brûleur de turbine à gaz
EP2948715B1 (fr) 2013-01-24 2019-04-17 Siemens Aktiengesellschaft Système de brûleur possédant des éléments de turbulence
EP2860453A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Brûleur à prémélange pour une turbine à gaz ayant une pointe de brûleur avec du refroidissement par impact interne
US20160252254A1 (en) * 2013-10-31 2016-09-01 Siemens Aktiengesellschaft Gas turbine burner hub with pilot burner
WO2015067482A1 (fr) * 2013-11-08 2015-05-14 Siemens Aktiengesellschaft Brûleur de turbine à gaz présentant des niveaux de combustible réglables séparément dans des déflecteurs de brûleur pilotes

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010061626A1 (de) * 2010-01-05 2011-07-07 General Electric Company, N.Y. Brennstoffzuführsysteme für Sekundärverbrennung

Also Published As

Publication number Publication date
RU2669439C1 (ru) 2018-10-11
CN107429918B (zh) 2019-09-06
DE102015206227A1 (de) 2016-10-13
WO2016162248A1 (fr) 2016-10-13
EP3250857A1 (fr) 2017-12-06
CN107429918A (zh) 2017-12-01

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