EP2058590A1 - Procédé de fonctionnement d'un brûleur - Google Patents

Procédé de fonctionnement d'un brûleur Download PDF

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Publication number
EP2058590A1
EP2058590A1 EP08168235A EP08168235A EP2058590A1 EP 2058590 A1 EP2058590 A1 EP 2058590A1 EP 08168235 A EP08168235 A EP 08168235A EP 08168235 A EP08168235 A EP 08168235A EP 2058590 A1 EP2058590 A1 EP 2058590A1
Authority
EP
European Patent Office
Prior art keywords
fuel
flow
hydrogen
burner
swirl
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
EP08168235A
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German (de)
English (en)
Other versions
EP2058590B1 (fr
Inventor
Adnan Eroglu
Richard Carroni
Stefano Bernero
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2058590A1 publication Critical patent/EP2058590A1/fr
Application granted granted Critical
Publication of EP2058590B1 publication Critical patent/EP2058590B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • F23R3/28—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
    • 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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the invention relates to a method according to the preamble of claim 1. It also relates to a burner for carrying out this method.
  • a per se known and technically controllable way to reduce the CO 2 emissions in combustion power plants consists in the removal of carbon from the fuels reaching combustion, which are accomplished before they are introduced into the combustion chamber.
  • Such pretreated fuels usually contain a large amount of H 2 and CO, and depending on the mixing ratios have calorific values, which are generally lower than those of natural gas.
  • Mbtu or Lbtu gases which are not readily suitable for use in conventional, designed for the combustion of natural gases such as natural gas burner, such as the EP 0 321 809 B1 .
  • WO 93/17279 as well as the EP 1 070 915 A1 are removable.
  • burners are described of the type of fuel premix, in each of which a conically expanding in the flow direction swirl flow of combustion air and mixed fuel is generated, the downstream as possible after the exit from the burner Achieving a homogeneous air-fuel mixture is unstable by the increasing swirl and merges into an annular swirl flow with backflow in the core.
  • liquid and / or gaseous fuel which forms in the interior of the premix burner, is introduced to form a homogeneous air-fuel mixture.
  • gaseous fuels are to be used as alternatives to or in combination with the combustion of conventional types of fuel for purposes of reduced pollutant, in particular CO 2 emissions, special requirements are imposed on the design of conventional premix burner systems. For example, synthesis gases for feeding into burner systems require a multiple fuel volume flow compared to comparable burners operated with natural gas, so that significantly different flow pulse ratios result.
  • WO 2006/058843 A1 are a method and a burner for the combustion of gaseous, liquid and hydrogen-containing or consisting of hydrogen fuel, synthesis gas, known.
  • a premix burner which has become known as a double-cone burner, with switched-after mixing section according to the EP 0 780 629 A2 used in FIGS. 2a and b is shown schematically in longitudinal section.
  • the premix burner arrangement provides a swirl generator 1, which widens conically in the longitudinal axis of the burner and is delimited by swirl shells 2. Axial and coaxial about the burner axis A of the swirl generator 1 means for supplying fuel are provided.
  • liquid fuel B fl reaches the swirling space through an injection nozzle 3 positioned along the burner axis A at the location of the smallest inner diameter of the swirl generator 1.
  • injection devices 5 are provided (see Fig. 2b ), which serve the further feed of synthesis gas B H2 .
  • the fuel-air mixture forming within the swirl generator 1 passes as swirling flow through a transition section 6, which provides the swirl flow stabilizing fluid 7, into a mixing tube 8, in which a completely homogeneous mixing of the forming fuel-air mixture before the ignitable fuel Air mixture is ignited within a downstream of the mixing tube 8 subsequent combustion chamber B. Due to an unsteady flow cross-sectional enlargement in the transition from the mixing tube 8 into the combustion chamber B, the swirling flow of the mixed fuel-air mixture bursts to form a remindströmzone in the form of a remindblasblase RB, in which adjusts a spatially stable flame front.
  • the airfoil forming along the burner is in Fig. 2a represented, which is characterized by a significant maximum velocity along the burner axis A, the amount of which is usually three to four times higher than those flow rates, which are able to form near the burner wall.
  • the synthesis gas B H2 according to the schematic longitudinal sectional view in Fig. 2b about 60 ° to the burner longitudinal axis A in the swirl chamber of the swirl generator 1.
  • Hydrogen-rich fuels with hydrogen contents of> 50% in particular typically have very high flame speeds and moreover have a much smaller volume-specific heat calorific value (MJ / m 3 ), so that much larger quantities of hydrogen-containing fuel are required for the burner Achieve a desired performance-related combustion heat must be supplied.
  • ignition phenomena already occur in the swirl chamber or along the mixing section of the burner, which are due to inadequate mixing of the hydrogenous fuel fed into the burner with a large volume flow.
  • Even in cases where no reignition phenomena occur insufficient mixing of the synthesis gas containing the hydrogen and the combustion air provides for diffusion-like combustion, ultimately leading to increased nitrogen oxide emissions.
  • the object of the present invention is a method for operating a premix burner and also specify a premix burner itself, in which the above disadvantages should be avoided. Furthermore, when operating with a fuel containing hydrogen, a so-called synthesis gas, it is necessary to ensure improved mixing with the burner air swirl flow as well as more stable flow conditions within the burner.
  • claim 9 is a device designed in accordance with the invention.
  • the concept of the invention advantageously further features are the subject of the dependent claims and the further description with reference to the exemplary embodiments. All claims are part of the further description.
  • the low volume-specific istwert and thereby required larger volume flow and the low density of the synthesis gas containing hydrogen are advantageously used insofar as on the one hand the large synthesis gas volume flow for selectively raising the flow velocity in the burner wall near flow areas to reduce the Flammen Wegzündrisiko downstream of the transition section.
  • the only low fuel density of the synthesis gas contributes to an improved mixing with the swirling flow of the combustion air, by centrifugal forces are used within the swirl flow to allow a radial mixing of the synthesis gas with the combustion air.
  • Synthesis gas is fed into radially outward areas of the swirl flow, it is due to the heavier Air components, which are driven radially outward by the centrifugal forces acting within the swirl flow, a displacement of the lighter synthesis gas in the vicinity of the axis relative to the burner axis.
  • the transition section between the region of the swirl generator and the downstream mixing tube serves primarily to transfer the swirl flow which widens conically within the swirl generator into the longitudinal axis of the burner into a cylindrical swirl flow which propagates along the mixing tube with a constant flow cross section.
  • the transfer of the flow form into a cylindrical swirl flow takes place by means of flow guide plates or flow guidance contours provided along the transition section.
  • the transition section contributes significantly to the fact that the flow velocity in the wall near areas along the mixing tube compared to the flow velocity in the field of burner or Mischrohrachse is much lower.
  • synthesis gas due to its own high volume flow rate, is particularly suitable for accelerating wall-oriented flow areas in a targeted way in terms of flow behavior.
  • the targeted feeding of the hydrogen-containing synthesis gas along the transition section is carried out in accordance with the solution such that the additional fuel feed in the direction of the transition section anyway passing swirling flow is admixed, ie the synthesis gas is fed with a suitable for forming inside the burner swirl flow tangentially selected as well as radial flow component relative to the burner longitudinal axis.
  • the fuel injection is adjusted to local flow angles to avoid the flashback risk due to increased turbulence.
  • the transition section is suitable for the injection of an additional synthesis gas stream, especially as the transition section is bounded by a transition piece formed with a sufficiently large wall thickness, through which a plurality of individual outlet openings for the synthesis gas supply can be provided.
  • the formation of the outlet openings as well as the individual synthesis gas supply channels connected to the outlet openings can be made almost anywhere according to shape and location without any design restrictions, especially as the transition piece offers sufficient space for these measures.
  • synthesis gas flows with a circular, elliptical, annular, almost rectangular or almost triangular flow cross-section, which exist for improved mixing with the inside of the burner Fuel-air swirl flow contributes.
  • Such a burner designed in accordance with the invention has, along the transition section, means for feeding in the synthesis gas containing at least the hydrogen.
  • Fig. 1 is a longitudinal sectional view of a solution according trained Vormischbrenners shown with a swirl generator 1, the swirl space is enclosed by two swirl shells in the form of Operakegelschalen 2, each mutually defining air inlet slots 4, is fed through the combustion air supply to form a swirl flow within the swirl space.
  • the swirl flow encloses a conically spreading liquid fuel column, which is discharged by remplissigbrennstoffaustrag through the centrally mounted fuel nozzle 3.
  • gaseous fuel preferably natural gas
  • the additional fuel feed in the region of the transition section 6 takes place either via circular uniformly distributed distributed individual outlet openings, all of which are supplied via a common supply line 10 with synthesis gas B H2 .
  • the fuel line 10 opens into a fuel reservoir 11 which surrounds the transition section 6 in a circular manner and from which the individual outlet openings 9 'of the fuel feed 9 are supplied with fuel.
  • the feeding of the synthesis gas B H2 takes place in such a way that the regions near the wall, in particular of the mixing tube 8 adjoining the transition section 6 downstream, are accelerated with regard to their flow behavior in order to reduce the risk of flashback. Equally, however, it is necessary to make the fuel feed with only slight adverse effects on the swirl flow forming within the swirl generator 1.
  • the longitudinal section shown is likewise the radial component, with which the fuel feed is introduced into the region of the transition section 6 as well as of the mixing tube 8 adjoining it downstream.
  • the slightly inclined towards the burner axis A direction of the fuel feed of the synthesis gas B H2 contributes to the improved mixing of the fuel with the air-fuel swirl flow, however, due to the centrifugal force caused by the rotational movement within the swirl flow, a radial exchange of the lighter, hydrogen-containing fuel , with the heavier air proportions of the Swirl flow is supported.
  • the longitudinal section in Fig. 1 It can be seen that immediately before entry into the combustion chamber B which adjoins the mixing tube 8 downstream, the hydrogen-containing fuel B H2 is mixed as homogeneously as possible over the entire flow cross-section.
  • the synthesis gas is additionally fed with a component which is tangential to the swirl flow, in order to minimize irritation to the swirl flow.
  • a component which is tangential to the swirl flow is on Fig. 3 referenced, which shows a cross-sectional view in the region of the transition section 6.
  • the inner contour of the transition section 6 is characterized by conically widening flow direction in the flow direction 7, which are optimized from a fluidic point of view and are able to convert conically expanding swirl flow in a propagating with constant flow cross-section swirl flow.
  • the reservoir 11 storing the synthesis gas is provided, which via the in FIG Fig. 1 shown supply line 10 is supplied with fuel.
  • supply line 10 is supplied with fuel.
  • a plurality of supply channels 12 are provided for feeding the fuel containing the hydrogen, via which the synthesis gas is fed into the interior of the transition section 6.
  • the spatial orientation of the individual fuel supply channels 12 is made such that the fuel discharge snuggles largely tangentially to the forming within the burner swirl flow D, without significantly affecting the swirl flow in their flow behavior.
  • FIG. 4 In a further longitudinal sectional view according to Fig. 4 are upstream of the outlet openings 9 'of the feed channels 12 Spülgaskanäle 13 provided by the additional air in a conventional manner along the wall of the downstream of the transition section 6 subsequent mixing tube 8 is discharged.
  • This in Fig. 4 illustrated embodiment provides that also 13 synthesis gas containing hydrogen is discharged through the purge gas channels, especially in cases where the burner is operated with natural gas and petroleum.
  • the additional use of already existing purge gas channels or film hole openings with hydrogen-containing fuel helps to control or influence the fuel concentration in the region of the burner wall, ie the wall along the mixing tube.
  • the solution according to the burner concept thus helps to reduce the risk of flashback significantly, on the one hand by a longitudinal wall of the mixing tube flow rate increase, on the other hand by an individual adjustment of the feed additional fuel, ie hydrogen-containing fuel with respect to the already forming within the swirl generator swirl flow, thus turbulent vortex formation can be largely avoided or reduced. Due to the much lower specific weight of the injected hydrogen-containing synthesis gas in comparison to the much larger proportion of air forming within the burner swirl flow causes the centrifugal force occurring due to the rotational movement, a radial mixing of the fed in the peripheral edge of the synthesis gas such that before the air Fuel swirl flow into the combustion chamber a complete mixing of the injected hydrogen is achieved.
  • the fuel supply lines and outlet openings can be designed and dimensioned as a function of the selected hydrogen-containing fuel.
  • Existing scavenging air supply openings for the formation of film layers close to the wall can likewise be used to feed hydrogen-containing synthesis gas. Due to the additional feed of synthesis gas only in the region of the transition section 6, the mean residence time of the hydrogen is much lower compared to a feed along the swirl generator, so that the burner operation can be carried out correspondingly safer.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP08168235.3A 2007-11-09 2008-11-04 Procédé de fonctionnement d'un brûleur Not-in-force EP2058590B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH17382007 2007-11-09

Publications (2)

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EP2058590A1 true EP2058590A1 (fr) 2009-05-13
EP2058590B1 EP2058590B1 (fr) 2016-03-23

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US (1) US9103547B2 (fr)
EP (1) EP2058590B1 (fr)
JP (1) JP5594951B2 (fr)

Cited By (5)

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CH701905A1 (de) * 2009-09-17 2011-03-31 Alstom Technology Ltd Verfahren zum Verbrennen wasserstoffreicher, gasförmiger Brennstoffe in einem Brenner sowie Brenner zur Durchführung des Verfahrens.
CN110651154A (zh) * 2017-08-21 2020-01-03 三菱日立电力系统株式会社 燃烧器及具备该燃烧器的燃气涡轮
WO2020259918A1 (fr) * 2019-06-25 2020-12-30 Siemens Aktiengesellschaft Dispositif de combustion pour turbine à gaz
CN114074020A (zh) * 2020-08-21 2022-02-22 北京国电智深控制技术有限公司 一种火电发电系统中磨煤机的控制方法、装置和系统
CN114110582A (zh) * 2022-01-25 2022-03-01 烟台市大昌燃气器具有限责任公司 一种助燃烧的燃烧器

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CN101910723B (zh) * 2007-11-27 2013-07-24 阿尔斯通技术有限公司 用于在预混燃烧器中燃烧氢气的设备
EP2220438B1 (fr) * 2007-11-27 2019-07-24 Ansaldo Energia Switzerland AG Procédé d'utilisation d'une centrale électrique à cycle combiné avec une installation de turbine à gaz par recours à un deuxième carburant riche en hydrogène
RU2480441C2 (ru) * 2008-03-05 2013-04-27 Басф Се Способ и устройство для частичного термического окисления углеводородов
JP2010230257A (ja) * 2009-03-27 2010-10-14 Dainichi Co Ltd 燃焼装置
EP2299178B1 (fr) * 2009-09-17 2015-11-04 Alstom Technology Ltd Procédé et système de combustion de turbine à gaz pour mélanger sans danger des carburants riches en H2 avec de l'air
CN104302976B (zh) * 2013-05-09 2017-05-17 施政 粉状固体燃料小型燃烧的系统及方法
JP6395363B2 (ja) * 2013-10-11 2018-09-26 川崎重工業株式会社 ガスタービンの燃料噴射装置
US9052109B1 (en) * 2014-12-12 2015-06-09 Infinitus Renewable Energy, LLC Pyrolytic gas processor and tire conversion system therefrom
US11020758B2 (en) * 2016-07-21 2021-06-01 University Of Louisiana At Lafayette Device and method for fuel injection using swirl burst injector
EP3290804A1 (fr) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brûleur avec alimentation d'air et de carburant incorporée dans une paroi du brûleur
US11555612B2 (en) * 2017-11-29 2023-01-17 Babcock Power Services, Inc. Dual fuel direct ignition burners
US10907832B2 (en) 2018-06-08 2021-02-02 General Electric Company Pilot nozzle tips for extended lance of combustor burner
DE102021210662A1 (de) * 2021-09-24 2023-03-30 Benninghoven Zweigniederlassung Der Wirtgen Mineral Technologies Gmbh Vorrichtung und Verfahren zum Trocknen von Material sowie Asphaltmischanlage mit einer derartigen Vorrichtung
US11815269B2 (en) 2021-12-29 2023-11-14 General Electric Company Fuel-air mixing assembly in a turbine engine
US11747018B2 (en) 2022-01-05 2023-09-05 General Electric Company Combustor with dilution openings
KR102599129B1 (ko) 2022-11-25 2023-11-07 순천대학교 산학협력단 부분 예혼합 유로계를 통한 역화방지용 수소 보일러

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WO1993017279A1 (fr) 1992-02-26 1993-09-02 United Technologies Corporation Bruleur de gaz a premelange
EP0780629A2 (fr) 1995-12-21 1997-06-25 ABB Research Ltd. Brûleur pour un générateur de chaleur
EP0833105A2 (fr) * 1996-09-30 1998-04-01 Abb Research Ltd. Brûleur à prémélange
DE19757189A1 (de) * 1997-12-22 1999-06-24 Abb Research Ltd Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
EP1070915A1 (fr) 1999-07-22 2001-01-24 Asea Brown Boveri AG Brûleur à prémélange
WO2005121648A1 (fr) * 2004-06-08 2005-12-22 Alstom Technology Ltd Bruleur a premelange a alimentation etagee en combustible liquide et procede pour faire fonctionner un bruleur a premelange
WO2006058843A1 (fr) 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
WO2006069861A1 (fr) * 2004-12-23 2006-07-06 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange

Cited By (10)

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CH701905A1 (de) * 2009-09-17 2011-03-31 Alstom Technology Ltd Verfahren zum Verbrennen wasserstoffreicher, gasförmiger Brennstoffe in einem Brenner sowie Brenner zur Durchführung des Verfahrens.
WO2011032935A3 (fr) * 2009-09-17 2012-03-29 Alstom Technology Ltd. Procédé pour brûler des combustibles gazeux, riches en hydrogène, dans un brûleur ainsi que brûleur pour la mise en oeuvre du procédé
US8549860B2 (en) 2009-09-17 2013-10-08 Alstom Technology Ltd Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method
DE112010003677B4 (de) 2009-09-17 2023-10-26 Ansaldo Energia Switzerland AG Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens
CN110651154A (zh) * 2017-08-21 2020-01-03 三菱日立电力系统株式会社 燃烧器及具备该燃烧器的燃气涡轮
CN110651154B (zh) * 2017-08-21 2022-03-29 三菱动力株式会社 燃烧器及具备该燃烧器的燃气涡轮
WO2020259918A1 (fr) * 2019-06-25 2020-12-30 Siemens Aktiengesellschaft Dispositif de combustion pour turbine à gaz
CN114074020A (zh) * 2020-08-21 2022-02-22 北京国电智深控制技术有限公司 一种火电发电系统中磨煤机的控制方法、装置和系统
CN114074020B (zh) * 2020-08-21 2024-02-02 北京国电智深控制技术有限公司 一种火电发电系统中磨煤机的控制方法、装置和系统
CN114110582A (zh) * 2022-01-25 2022-03-01 烟台市大昌燃气器具有限责任公司 一种助燃烧的燃烧器

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US9103547B2 (en) 2015-08-11
EP2058590B1 (fr) 2016-03-23
JP2009121806A (ja) 2009-06-04
JP5594951B2 (ja) 2014-09-24
US20090123882A1 (en) 2009-05-14

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