WO2015062962A1 - Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote - Google Patents

Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote Download PDF

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Publication number
WO2015062962A1
WO2015062962A1 PCT/EP2014/072741 EP2014072741W WO2015062962A1 WO 2015062962 A1 WO2015062962 A1 WO 2015062962A1 EP 2014072741 W EP2014072741 W EP 2014072741W WO 2015062962 A1 WO2015062962 A1 WO 2015062962A1
Authority
WO
WIPO (PCT)
Prior art keywords
burner
fuel
pilot
nozzles
channels
Prior art date
Application number
PCT/EP2014/072741
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Tobias Krieger
Patrick Lapp
Andreas Mann
Stefan Reich
Kai-Uwe Schildmacher
Sascha Staring
Daniel Vogtmann
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 US15/030,916 priority Critical patent/US20160252254A1/en
Priority to EP14793808.8A priority patent/EP3008390A1/fr
Publication of WO2015062962A1 publication Critical patent/WO2015062962A1/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
    • F23R3/343—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
    • 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
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the invention relates to a burner assembly, in particular a burner assembly with a main burner and a pilot burner, and refers to the mixture of fuel with air.
  • a burner assembly in particular a burner assembly with a main burner and a pilot burner, and refers to the mixture of fuel with air.
  • fuel is metered out as finely as possible and fed to the combustion air.
  • both the combustion air and the fuel by constructive measures in
  • Twisting movements offset This is typically done mainly by curved blades and fuel nozzles.
  • Pollutants such as nitrogen oxides (NO x) are mainly Exploitation ⁇ degree affected by the mixing ratio of fuel to air and the combustion. A complete combustion of the fuel is desirable wrestlers to pollutants ver ⁇ .
  • Gaseous fuels such as natural gas or synthesis gas, but also liquid fuels are suitable as fuel.
  • liquid fuel oil has mainly influenced the nozzle geometry in combination with the
  • Blade turbulence its mixing with air. Another actively influencing, for example, the depth of penetration of the fuel into the air flow or the turbulence of the fuel and thus finds an optimized mixing üb ⁇ SHORT- not take place.
  • the gas is emptied, for example, through holes in a swirl blade and with the
  • Compressor air premixed and twisted Both fuels, gas and oil, typically use a pilot burner to stabilize the premix flame.
  • a pilot burner For oil, it is an oil diffusion burner, for gas, it is a pilot gas burner.
  • the object of the invention is to provide said device wei ⁇ terzuentwickeln, so that a complete combustion as possible is achieved in the operation of the device.
  • a burner assembly for a combustion chamber in particular a gas turbine combustion chamber for firing fluidic fuels, comprising a main burner and a centrally therein reasonable associated pilot burner, which serves to ignite and / or to stabilize the combustion of the main burner, the main ⁇ burner a to arranged the pilot burner centrally ⁇ rale fuel supply arrangement, an annular air passage surrounding the central fuel supply arrangement for the supply of combustion air, primary fuel nozzle for injecting a substantially gaseous fuel into the annular air passage, wherein the first fuel nozzles are fed from a first fuel distributor in the central fuel supply arrangement, and second fuel nozzles for injecting a substantially liquid fuel into the annular air passage, the second fuel nozzles being fed by a second fuel distributor in the central fuel supply arrangement, channels v esigned are branched from Minim ⁇ least one of the fuel manifold and open out into the pilot burner and the pilot burner
  • the pilot burner comprises a pilot annular air duct for supplying combustion air and the channels open into this pilot annular air duct.
  • the channels branch off from the second fuel distributor and have nozzles at their ends which open into the pilot burner.
  • the second fuel distributor for injecting a substantially liquid fuel, so oil, is mechanically particularly stressed so that it is particularly advantageous here, if the nozzles cavitation ⁇ free and to exchange as needed can be screwed.
  • the annular air channel has swirl blades and the first fuel nozzles are arranged in these swirl blades.
  • the addition of fuel from the central fuel supply arrangement does not replace the independent supply of gas or oil in the pilot burner, but provides in combination with these for additional fuel enrichment why in advantageous embodiments of the pilot burner next to a channel independent gas supply channel also one of the Channels independent oil supply channel has.
  • the additional mass flows from the gas or oil distributors according to the invention are mixed with the compressor air in the pilot gas line and then combined with the fuel in the pilot burner.
  • An implementation of the invention can also take place in an existing design by the simple introduction of bores or nozzles.
  • the burner assembly 1 has a main axis 19 and includes a pilot burner 3 and a pilot burner 3 concentrically surrounding the main burner 2.
  • Both pilot burner 3 and main burner 2 can optionally with gaseous and / or liquid fuels, such as. Natural gas or fuel oil, operated.
  • the pilot burner 3 then includes as fuel channels an inner oil supply channel 18 and a concentrically surrounding this inner, annular gas supply channel 17. This is in turn surrounded by a pilot annular air channel 13 for the supply of combustion air 14 kon ⁇ centric.
  • a ge ⁇ One suitable ignition system can also be arranged in or on this pilot ring air duct 13 (not shown in the figure).
  • pilot annular air channel 13 further swirl blades 20 are arranged, which fuel nozzles 21 for supplying a fuel to a stream 14 of an oxygen-containing Ga ⁇ ses, typically having air.
  • the pilot burner 3 surrounding the main burner 2 comprises a relative to the main axis 19 of radially outer annular air passage 5 for the combustion air 6, extend through the several swirl ⁇ shovel 16 of a swirl vane.
  • Swirl vanes 16 have as fuel inlet first fuel nozzles 7, can be injected through the fuel gas into the air flowing through the annular air duct 5 6 through the fuel gas.
  • the first fuel nozzles 7 are fed via a first fuel distributor 8 in a central fuel supply arrangement 4.
  • a second fuel distributor 10 in the central fuel supply assembly 4 typically supplies second fuel nozzles 9 with oil.
  • the task of the pilot burner 3 is to maintain a stable combustion operation in the burner assembly 1, since this is usually operated with a tendency to instabilities lean mixture.
  • both channels 11 are now provided according to the invention, which branch off from the first fuel distributor 8 for the gas supply and open into the pilot burner 3, as well as channels 12 which branch off from a second fuel distributor 10 for oil.
  • the channels 12 have at their opening into the pilot burner 3 ends nozzles 15.
  • the channels 11, 12 are uniformly distributed over a circumference of the pilot lot-annular air channel 13 is distributed, and may be designed as a simple Boh ⁇ requirements.

Landscapes

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

Abstract

L'invention concerne un ensemble de brûleurs (1) destiné à une chambre de combustion, en particulier une chambre de combustion de turbine à gaz, pour brûler des combustibles fluides, comprenant un brûleur principal (2) et un brûleur pilote (3) qui est disposé à l'intérieur et au centre et qui sert à allumer et/ou stabiliser la combustion du brûleur principal ( 2), le brûleur principal (2) comprenant un ensemble d'alimentation en combustible central (4) disposé autour du brûleur pilote (3), un canal d'air annulaire (5) entourant l'ensemble d'alimentation en combustible central (4) et servant à l'alimentation en air de combustion (6), des premiers injecteurs de combustible (7) servant à injecter un combustible sensiblement gazeux dans le conduit d'air annulaire (5), les premiers injecteurs de combustible (7) étant alimentés par un premier distributeur de combustible (8) placé dans l'ensemble d'alimentation en combustible central (4), et des seconds injecteurs (9) servant à injecter un combustible sensiblement liquide dans le conduit d'air annulaire (5), lesdits seconds injecteurs de combustible (9) étant alimentés par un second distributeur de combustible (10) placé dans l'ensemble d'alimentation en combustible central (4), des conduits (11, 12) étant prévus qui viennent de l'un au moins des distributeurs de combustible (8, 10) et qui débouchent dans le brûleur pilote (3).
PCT/EP2014/072741 2013-10-31 2014-10-23 Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote WO2015062962A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US15/030,916 US20160252254A1 (en) 2013-10-31 2014-10-23 Gas turbine burner hub with pilot burner
EP14793808.8A EP3008390A1 (fr) 2013-10-31 2014-10-23 Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013222152.5 2013-10-31
DE102013222152 2013-10-31

Publications (1)

Publication Number Publication Date
WO2015062962A1 true WO2015062962A1 (fr) 2015-05-07

Family

ID=51866131

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/072741 WO2015062962A1 (fr) 2013-10-31 2014-10-23 Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote

Country Status (3)

Country Link
US (1) US20160252254A1 (fr)
EP (1) EP3008390A1 (fr)
WO (1) WO2015062962A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016162248A1 (fr) * 2015-04-08 2016-10-13 Siemens Aktiengesellschaft Ensemble brûleur

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108474558B (zh) * 2015-12-30 2020-08-04 通用电气公司 用于双燃料燃烧器的液体燃料喷嘴
EP3361159B1 (fr) 2017-02-13 2019-09-18 Ansaldo Energia Switzerland AG Procédé de fabrication d'un ensemble brûleur pour une chambre de combustion de turbine à gaz et ensemble brûleur pour une chambre de combustion de turbine à gaz
US10816210B2 (en) * 2017-09-28 2020-10-27 General Electric Company Premixed fuel nozzle
KR102382634B1 (ko) * 2020-12-22 2022-04-01 두산중공업 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0193838A2 (fr) * 1985-03-04 1986-09-10 Siemens Aktiengesellschaft Disposition de brûleur pour installations de combustion, en particulier pour chambres de combustion d'installations de turbines à gaz ainsi que procédé de sa mise en oeuvre
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

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2264370B1 (fr) * 2009-06-16 2012-10-10 Siemens Aktiengesellschaft Agencement de brûleur pour une installation de combustion destinée à la combustion de combustibles fluidiques et procédé de fonctionnement d'un tel agencement de brûleur
US8418469B2 (en) * 2010-09-27 2013-04-16 General Electric Company Fuel nozzle assembly for gas turbine system
EP2439447A1 (fr) * 2010-10-05 2012-04-11 Siemens Aktiengesellschaft Buse à combustible, chambre de combustion de turbine à gaz et brûleur doté d'une telle buse à combustible
US20120210717A1 (en) * 2011-02-21 2012-08-23 General Electric Company Apparatus for injecting fluid into a combustion chamber of a combustor
US8905333B1 (en) * 2011-05-24 2014-12-09 Mainstream Engineering Corporation Diesel injector and method utilizing focused supercavitation to reduce spray penetration length
DE102012216080A1 (de) * 2012-08-17 2014-02-20 Dürr Systems GmbH Brenner
US9316154B2 (en) * 2013-03-07 2016-04-19 Solar Turbines Incorporated Gas turbine fuel injector with metering cavity

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0193838A2 (fr) * 1985-03-04 1986-09-10 Siemens Aktiengesellschaft Disposition de brûleur pour installations de combustion, en particulier pour chambres de combustion d'installations de turbines à gaz ainsi que procédé de sa mise en oeuvre
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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016162248A1 (fr) * 2015-04-08 2016-10-13 Siemens Aktiengesellschaft Ensemble brûleur

Also Published As

Publication number Publication date
US20160252254A1 (en) 2016-09-01
EP3008390A1 (fr) 2016-04-20

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