WO2016162248A1 - Ensemble brûleur - Google Patents

Ensemble brûleur Download PDF

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Publication number
WO2016162248A1
WO2016162248A1 PCT/EP2016/056892 EP2016056892W WO2016162248A1 WO 2016162248 A1 WO2016162248 A1 WO 2016162248A1 EP 2016056892 W EP2016056892 W EP 2016056892W WO 2016162248 A1 WO2016162248 A1 WO 2016162248A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
burner
annular air
tube
nozzles
Prior art date
Application number
PCT/EP2016/056892
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Tobias Krieger
Patrick Lapp
Andreas Mann
Simon Purschke
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to CN201680019818.5A priority Critical patent/CN107429918B/zh
Priority to EP16713412.1A priority patent/EP3250857B1/fr
Priority to RU2017136855A priority patent/RU2669439C1/ru
Publication of WO2016162248A1 publication Critical patent/WO2016162248A1/fr

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
    • F23R3/34—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
    • 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
    • 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 firing fluid fuels.
  • pilot premix burner In a burner with, for example, main premix burner and pilot premix burner, these are primarily the fuel mass flows of the main premix burner and the pilot premix burner. Depending on the setting, about 90% -95% of the fuel mass flow passes through the main premix burner, the remainder through the pilot premix burner. It is known that a change (even in the percentage range) of the pilot gas mass flow has a significant influence on emissions and buoyancy. However, such a rule by a single fuel level in Pilotvormischbrenner is be ⁇ borders.
  • both stages can be controlled independently.
  • both pilot fuel ⁇ levels can be integrated in pilot burner blades to allow for both stages, a good mixing of fuel and air.
  • Bohrungsmus ⁇ ters so the radial fuel distribution can be actively influenced during operation and thus influence on emissions and combustion stability are taken. This makes it possible to extend the corridors, through which must be maneuvered when starting and stopping the machine, and the emissi ⁇ ons- and stability behavior, especially in the partial load range, can be improved.
  • WO 2014/114533 A1 discloses a burner arrangement with a diffusion gas passage lying on the axis of the burner arrangement.
  • This passage could be ⁇ example be used by a tube-in-tube design for the fuel supply of a second stage in the pilot burner.
  • the tube-in-tube construction would then have to be relieved by a complex and therefore comparatively expensive compensator.
  • the object of the invention is therefore to provide a burner assembly of the type mentioned, which allows a beträchtli ⁇ che improvement in terms of emissions and stability and at the same time as simple and inexpensive to manufacture and assemble.
  • the invention solves this task by at a Derar ⁇ term burner assembly for a combustion chamber, in particular a gas turbine combustion chamber for firing fluidic fuels, comprising a main burner and a reasonable centrally therein arranged pilot burner, which serves to ignite and / or stabilize the combustion of the main burner, the main ⁇ burner comprising a first annular air duct for supplying combustion air and first fuel nozzles for injecting a fuel in the first annular air duct, the Pilotbren ⁇ ner comprising a second annular air duct Supply of combustion air and a burner head with second fuel ⁇ fuel nozzles for injecting a fuel in the second annular air passage, wherein the second fuel nozzles are provided as separately controllable first and second fuel stages, for supplying fuel to the first and second fuel stages,
  • the emission and stability behavior of the torch assembly is improved, and it can be dispensed with the comparatively complicated and expensive as ⁇ pipe-in-pipe construction with com- expansion joint.
  • the first and second deep hole bores are arranged at different radii relative to the longitudinal axis of the burner support tube in the pipe wall, so that
  • Fuel can be supplied directly via straight bores of a respective fuel stage.
  • the preparation of sol ⁇ cher bores is comparatively cost effective.
  • the at least one first and one second deep hole bore open into a respective fuel distributor channel of a fuel stage.
  • the number of deep hole bores can be smaller than the number of fuel nozzles per fuel stage.
  • the burner support tube has on its axis a diffusion gas passage, the also flows into the burner head, so that a Diffu ⁇ sion operation is possible.
  • the burner carrier tube is connected in the flow direction of a fuel upstream of the burner head to a carrier plate, wherein the carrier plate has fuel ring distributor, of which the at least one first and one second deep hole bore abzwei ⁇ conditions.
  • the carrier plate has fuel connections which open into the fuel ring manifolds.
  • FIG. 2 shows a known pilot burner
  • FIG. 3 shows a downstream detail of the pilot burner
  • FIG. 2 is a diagrammatic representation of FIG. 1
  • FIG. 4 shows an upstream detail of the pilot burner
  • FIG. 2 is a diagrammatic representation of FIG. 1
  • FIG. 5 shows a sectional view of the burner arrangement according to the invention, showing the inner channel
  • FIG. 6 is a sectional view of the burner assembly according to the invention showing the outer channel
  • Figure 7 is a side view of the downstream end of the
  • Burner support tube of the burner assembly Figure 8 shows a section through the support plate and outer channel of
  • FIG. 9 shows a section through carrier plate and connection for the outer channel and through the inner channel of the burner carrier tube, FIG.
  • Figure 11 is a Einschraubverbinder with through hole and radial openings in the external thread in the
  • FIG. 12 is a sectional view of a screw-in connector with a through bore and radial openings in the external thread
  • FIG. 13 shows a detailed view of the burner head with transition to the burner support tube and Figure 14 is an oblique view of the upstream side of the burner head.
  • FIG. 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 centrally therein, which serves to ignite and / or stabilize the combustion of the main burner 2.
  • the main burner 2 comprises a first annular air passage 4 for supplying combustion air and first fuel nozzles 5 for injecting a fuel into the first annular air passage 4.
  • the pilot burner 3 comprises a second annular air passage 6 for supplying combustion air and second fuel nozzles 8 for injecting a fuel into the second annular air passage 6th
  • the second fuel nozzles 8 are first and second
  • Fuel stages 9, 10 are provided, each fuel stage 9, 10 has its own fuel supply.
  • the first annular air channel 4 has first swirl vanes 30, in which the first fuel nozzles 5 are arranged.
  • the second annular air channel 6 has second swirl blades 31.
  • the second fuel nozzles 8 are arranged, which, as already stated, in a first and a second fuel stage 9, 10 split.
  • Figure 2 shows a known pilot burner 32 with a central diffusion gas passage 20, in which a tube 33 is arranged, wherein between an inner wall 34 of the Diffusionsgaspas ⁇ sage 20 and a tube outer wall 35, an annular channel 36 for the Fuel supply to the second fuel stage 10 is formed.
  • This tube-in-tube construction is relieved by a compensator 37.
  • FIG. 3 shows a downstream detail of the pilot burner 3 from FIG. 2, in particular the pilot burner head 7 with the fuel supply for the first and second fuel stages 9, 10.
  • FIG. 4 shows an upstream detail of the pilot burner 3 from FIG. 2, in particular the compensator 37 of the tube in-pipe construction.
  • FIGS. 5 and 6 the pilot burner 3 according to the invention is shown in different sectional planes.
  • FIG. 5 shows the section through second deep hole bores 15, which represent the inner channel 38
  • FIG. 6 shows the corresponding view with first deep hole bores 14 for the outer channel 39.
  • the first and second deep hole bores 14, 15 are at different radii 16, 17 are arranged with respect to the longitudinal axis 13 of the burner support tube 11 in the tube wall 12.
  • FIGS. 5 and 6 show that the at least one first and one second deep hole bores 14, 15 open into a respective fuel distributor 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 assembly 1. It can be seen the ends of the first and second deep holes 14, 15 of the inner and outer channel 38, 39th
  • Figures 8, 9 and 10 show sectional detail views in the region of the support plate 21 of the pilot burner 3.
  • Figure 8 shows a section through the Trä ⁇ carrier plate 21 ler with the first and second Brennstoffringvertei- 22, 23 and the outer channel formed by deep-hole bores 14 39 in the tube wall 12 of the burner support tube eleventh
  • FIG. 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.
  • FIG. 9 shows a section through the serious fuel port 24 to the first fuel ring distributor 22 for the outer channel 39.
  • Figure 10 finally shows a section through the Trä- carrier plate 21 with the second fuel port 25 for two ⁇ th annular fuel manifold 23 for the inner channel 38. It can be seen in Figure 10 that the second fuel ⁇ ring distributor 23 relatively close to the inner channel 38 lies below the surface of the carrier plate 21.
  • the fuel connection 25 is realized via a screw-in connector 26 with a through-hole 27 and essentially radial openings 28 in the external thread 29.
  • Figures 11 and 12 show such a Einschraubverbinder 26 in plan view and in section.
  • FIG. 13 shows a detailed view of the burner head 7 with transition to the burner support tube 11.
  • the burner head 7, which is shown in the oblique view in FIG. 14, is the same as in FIG. 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)

Abstract

L'invention concerne un ensemble brûleur (1) pour une chambre de combustion, en particulier une chambre de combustion de turbine à gaz, servant à brûler des combustibles fluidiques. L'ensemble brûleur comprend un brûleur principal (2) et un brûleur pilote (3) disposé dans ce dernier au centre, lequel sert à allumer et/ou à stabiliser la combustion du brûleur principal (2). Le brûleur principal (2) comprend un premier canal d'air annulaire (4) servant à amener de l'air de combustion et des premières buses de combustible (5) servant à injecter un combustible dans le premier canal d'air annulaire (4). Le brûleur pilote (3) comprend un deuxième canal d'air annulaire (6) servant à amener de l'air de combustion. L'ensemble brûleur comprend également une tête de brûleur (7) pourvue de deuxièmes buses de combustible (8) servant à injecter un combustible dans le deuxième canal d'air annulaire (6). Les deuxièmes buses de combustible (8) sont prévues sous la forme de premiers et de deuxièmes étages de combustible (9, 10) pouvant être commandés séparément, un tuyau de support de brûleur (11) pourvu d'une paroi tubulaire (12) et se raccordant à la tête de brûleur (7) étant prévu pour amener du combustible aux premiers et aux deuxièmes étages de combustibles (9, 10). La paroi tubulaire (12) comporte, de manière parallèle par rapport à l'axe longitudinal (13) du tuyau de support de brûleur (11), au moins un premier et un deuxième alésage profond (14, 15) pour l'alimentation en combustible des premiers et deuxièmes étages de combustible (9, 10).
PCT/EP2016/056892 2015-04-08 2016-03-30 Ensemble brûleur WO2016162248A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201680019818.5A CN107429918B (zh) 2015-04-08 2016-03-30 燃烧器装置
EP16713412.1A EP3250857B1 (fr) 2015-04-08 2016-03-30 Agencement de brûleur
RU2017136855A RU2669439C1 (ru) 2015-04-08 2016-03-30 Система горелок

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015206227.9 2015-04-08
DE102015206227.9A DE102015206227A1 (de) 2015-04-08 2015-04-08 Brenneranordnung

Publications (1)

Publication Number Publication Date
WO2016162248A1 true WO2016162248A1 (fr) 2016-10-13

Family

ID=55646580

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2016/056892 WO2016162248A1 (fr) 2015-04-08 2016-03-30 Ensemble 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112283706A (zh) * 2020-11-20 2021-01-29 华侨大学 一种多枪旋流式低氮燃烧器

Families Citing this family (1)

* 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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2354662A2 (fr) * 2009-12-29 2011-08-10 Ansaldo Energia S.p.A. Brûleur pour turbine à gaz et turbine à gaz avec un tel brûleur
WO2014114533A1 (fr) * 2013-01-24 2014-07-31 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
WO2015062962A1 (fr) * 2013-10-31 2015-05-07 Siemens Aktiengesellschaft Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote
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

Family Cites Families (9)

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Publication number Priority date Publication date Assignee Title
EP0580683B1 (fr) * 1991-04-25 1995-11-08 Siemens Aktiengesellschaft Bruleur, en particulier pour turbines a gaz, pour la combustion peu polluante du gaz de houille et d'autres combustibles
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
US20110162375A1 (en) * 2010-01-05 2011-07-07 General Electric Company Secondary Combustion Fuel Supply Systems
EP2503240A1 (fr) * 2011-03-22 2012-09-26 Siemens Aktiengesellschaft Brûleur de turbine à gaz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2354662A2 (fr) * 2009-12-29 2011-08-10 Ansaldo Energia S.p.A. Brûleur pour turbine à gaz et turbine à gaz avec un tel brûleur
WO2014114533A1 (fr) * 2013-01-24 2014-07-31 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
WO2015062962A1 (fr) * 2013-10-31 2015-05-07 Siemens Aktiengesellschaft Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112283706A (zh) * 2020-11-20 2021-01-29 华侨大学 一种多枪旋流式低氮燃烧器
CN112283706B (zh) * 2020-11-20 2024-05-14 华侨大学 一种多枪旋流式低氮燃烧器

Also Published As

Publication number Publication date
DE102015206227A1 (de) 2016-10-13
RU2669439C1 (ru) 2018-10-11
EP3250857B1 (fr) 2020-01-01
EP3250857A1 (fr) 2017-12-06
CN107429918B (zh) 2019-09-06
CN107429918A (zh) 2017-12-01

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