EP1510755B1 - Brûleur avec lance et alimentation étagée en carburant - Google Patents

Brûleur avec lance et alimentation étagée en carburant Download PDF

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Publication number
EP1510755B1
EP1510755B1 EP04104099.9A EP04104099A EP1510755B1 EP 1510755 B1 EP1510755 B1 EP 1510755B1 EP 04104099 A EP04104099 A EP 04104099A EP 1510755 B1 EP1510755 B1 EP 1510755B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
combustion air
fuel outlet
openings
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.)
Not-in-force
Application number
EP04104099.9A
Other languages
German (de)
English (en)
Other versions
EP1510755A1 (fr
Inventor
Adnan Eroglu
Peter Flohr
Christian Oliver Paschereit
Peter Stuber
Martin Zajadatz
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
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Publication of EP1510755A1 publication Critical patent/EP1510755A1/fr
Application granted granted Critical
Publication of EP1510755B1 publication Critical patent/EP1510755B1/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
    • 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
    • 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 invention relates to a burner, consisting essentially of a swirl generator for a combustion air flow, with a conical swirl space and means for introducing fuel into the combustion air flow, wherein the swirl generator combustion air inlet openings for the tangential entering into the conical swirl chamber combustion air flow and the Means for introducing fuel into the combustion air flow include a first fuel supply having a first group of substantially arranged in the direction of the burner axis fuel outlet openings for a first premix fuel.
  • the conical swirl generator composed of several shells produces a closed swirl flow in the conical head, which becomes unstable due to the increasing swirl along the conically expanding swirl space and merges into an annular swirl flow with backflow in the core.
  • the shells of the swirl generator are assembled in such a way that tangential air inlet slots for combustion air are formed along the burner axis.
  • Supplements for the premix gas, ie the gaseous fuel, which distributed in the direction of the burner axis are provided on the inflow edge of the conical shells formed thereby Have outlet openings for the premixed gas.
  • the gas is injected through the outlet openings or bores transversely to the air inlet gap. This injection, in conjunction with the swirl generated in the swirl space of the combustion air-fuel gas flow to a good mixing of the fuel or premixed gas with the combustion air. Good mixing is the prerequisite for low NO x values in the combustion process in premix burners of this kind.
  • a burner for a heat generator which has an additional mixing section for further mixing of fuel and combustion air following the swirl generator.
  • This mixing section can be designed, for example, as a downstream tube, into which the flow emerging from the swirl generator is transferred without appreciable flow losses. Through this additional mixing section, the degree of mixing can be further increased and thus the pollutant emissions can be reduced.
  • One possible measure for encountering the risk of flashback is to provide a fuel injection which is as far downstream as possible from the premix section, which, however, considerably shortens the mixing section to form a completely mixed fuel-air mixture.
  • the EP 0 918 191 A1 provides to improve the degree of mixing between fuel and air in the flow direction through the combustion air inlet openings set back injection of fuel, so that there is a partial mixing between fuel and combustion air before they flow into the other interior of the swirl generator.
  • extensive and structurally complicated flow-related measures must be taken within the burner structure.
  • the burner's performance in terms of flame stability, emissions and the occurrence of thermoacoustic pulsations in burners are subject to far greater instabilities for the operation of medium and smaller power gas turbine engines than for burners designed for high performance gas turbine engines ,
  • WO 01/9675 describes a dual-cone burner with two independent fuel feeds.
  • the invention has for its object to design a burner of the type mentioned, in particular according to the preamble of claim 1, such that the performance of the burner should be designed to be stable in the largest possible operating range, ie the burner is independent of the current load a have as constant combustion stability. Moreover, the burner should also be able to be operated stably with different fuel types or qualities and in particular at lower burner outputs.
  • the inventive measures should be simple and inexpensive to implement and, moreover, allow the possibility of retrofitting on already existing burners. Within the large operating range required above, the burner is intended to ensure minimized emission of pollutants as well as maximum efficiency while forming a stable flame.
  • the inventively constructed burner according to the features of the preamble of claim 1 is characterized by the combination of two measures.
  • the burner has at least a second fuel supply with at least a second group of fuel outlet openings arranged substantially in the direction of the burner axis for a second premix fuel quantity, which can be acted upon by fuel independently of the first fuel supply.
  • it is possible to individually set the fuel supply together with the combustion supply air into the conical swirl space in at least two separate spatial areas along the burner axis within the swirl space and thereby produce individual fuel-air mixtures within the swirl space depending on the current burner load.
  • a burner lance protrudes along a burner axis from the sides of the swirl space with the smallest swirl space cross section into the swirl space and has at least one fuel outlet opening within the burner lance, through which fuel, preferably liquid fuel, can be discharged along the burner axis.
  • the burner lance which projects into this at least 50% of the axial extent of the swirl space, on the one hand due to their preferably round outer contour to stabilize the swirling flow forming swirling dynamics within the swirl space, which ultimately also the flame front within the combustion chamber is stabilized, on the other hand, preferably oriented in the burner longitudinal axis fuel outlet opening within the burner lance an additional Ausdüsung of fuel in the swirl space, which merges with the introduced via the tangential combustion air inlet openings along the swirl generator combustion air and the stable formation of a downstream in contributes to the combustion chamber forming flame front.
  • the advantage of the burner designed according to the invention can be seen in the multistage fuel feed into the swirl chamber, whereby the burner behavior can be adjusted very finely dosed depending on the burner load.
  • the presence of the burner lance within the swirl chamber which constitutes a type of flow body or flow body for the fuel-air mixture forming along the swirl space along the swirl space, decisively reduces the extent of the thermoacoustic pulsations that usually occur as a result of the combustion. Not only does this reduce the risk of flashback into the mixing zone of the premix burner, but the flame aerodynamically stabilized by the burner lance contributes to complete combustion of the fuel fraction in the fuel-air mixture, which ultimately can significantly reduce defective emissions.
  • the inventive integration of the burner lance in an at least two-stage premix burner burner operation for each type of fuel is possible.
  • provided within the swirl space burner lance allows the escape of liquid fuel, preferably axially in the direction of the burner axis.
  • the burner lance provides at its burner lance tip the fuel discharge opening surrounded by an annular opening through which combustion air can be discharged along the burner axis, so that the fuel discharge is conically lined by the combustion air through the fuel discharge opening a centered Introduction of a liquid fuel-air mixture along the swirl space is created, in addition to the spirally propagating along the burner axis gaseous fuel-air mixture.
  • the cone-shaped swirl generator provides at least two groups of fuel outlet openings along its combustion air inlet openings, through which individually selectable premix fuel quantities can each be fed into the swirl space.
  • This makes it possible to achieve individual mixture distributions and mixing qualities, taking into account different combustion boundary conditions.
  • a balance of different Wobbelwar be achieved by, for example, discharged via the first fuel supply a certain volume flow of fuel and the rest of the volume flow required for a certain power range is applied via the second fuel feeds.
  • the burner according to the invention is not limited to just two fuel feeds with correspondingly arranged in the direction of the burner axis fuel outlet openings. Rather, the burner concept according to the invention also includes three-, four- and multi-stage fuel feeds with corresponding fuel outlet openings, each separated and from each other with gaseous fuel for a fuel outlet in the swirl space for forming a fuel-air mixture spreading along the burner axis are acted upon.
  • the groups of the fuel outlet openings arranged essentially in the direction of the burner axis, which are each supplied individually with fuel via fuel feeds, are arranged in series in burner axles in corresponding exemplary embodiments or are designed to be partially overlapping at least in the burner axis.
  • the special group-trained arrangements of fuel outlet openings along the burner axis in the combustion air inlet openings are basically no design-related limits set.
  • the burner is preferably operated in the context of a heat generator, such as in a gas turbine, then in a starting phase of the gas turbine all the fuel can be supplied via the first fuel supply.
  • the fuel can be divided, for example, to a first and one or more second fuel feeds.
  • the second fuel outlet openings of the second fuel feed can have different mutual distances or flow cross sections compared to the first fuel outlet openings.
  • the respective fuel discharge openings may also have the same mutual distances, but may be arranged offset to one another. This leads to a more uniform injection of Vormischbrennschers in the swirl chamber.
  • the first fuel outlet openings over the entire axial extent of the combustion air inlet openings, the second fuel outlet openings may be arranged only in a certain axial portion. In the same way it is also possible, the first fuel outlet openings only in a first axial Provide portion and the second fuel outlet openings only in a subsequent to the first portion second axial portion - or vice versa.
  • premix fuel for the independent application of the premix fuel to the first and the second fuel feed, these are equipped with different connections.
  • means are further provided for independently controlling or controlling the premix fuel supply to the first and second fuel feeds.
  • the different supply can be controlled for example by a suitable control valve.
  • the premix burner has a swirl space 2 which widens conically starting from the burner head 1 and which is radially surrounded by a conical swirl generator 2, each consisting of at least two premix burner shells which have at least two combustion air inlet openings (not shown) for a tangential into the conical swirl space 2 include incoming combustion air flow.
  • a conical swirl generator 2 each consisting of at least two premix burner shells which have at least two combustion air inlet openings (not shown) for a tangential into the conical swirl space 2 include incoming combustion air flow.
  • a first group 4 of substantially arranged in the direction of the burner axis A fuel outlet openings are provided, which are supplied via a not shown first fuel supply with preferably gaseous fuel. Axially downstream of the first group 4 of the fuel outlet openings then there is a second group 5 of fuel outlet openings, which separately via a second fuel supply a second Vormischbrunstoffmenge can be supplied.
  • the burner assembly shown in the figure is a so-called two-stage premix burner, wherein the order of the steps depends on the number of separate groups of separately supplied with gaseous fuel fuel outlet openings.
  • embodiments are conceivable in which three and more groups of fuel outlet openings are arranged along the combustion air inlet openings.
  • Such premixed burners allow, depending on the respective operating conditions, i. be it start, part load or full load conditions, an optimized fuel supply into the swirl chamber 2, whereby an optimized combustion is ensured.
  • gaseous fuel is fed into the swirl space via the first group 4 of the fuel outlets.
  • the fuel supply via the first stage of the fuel outlet openings 4 is supplemented by an independently regulated second fuel feed via the second stage of the fuel outlet openings 5.
  • an exclusive Brennstöff feed over the second stage of the fuel outlet openings 5.
  • the centrally projecting from the burner head 1 into the swirl chamber 2 inside burner lance 6 is due to its aerodynamically shaped round outer contour for stabilization of forming within the swirl chamber 2
  • Fuel-air vortex flow the axialward according to longitudinal sectional view to the right in the subsequent, not shown combustion chamber propagates. Due to the aerodynamically stabilizing effect of the burner lance 6 on the forming fuel-air vortex flow, a spatially stable flame front is supported within the combustion chamber. Also, the burner lance the commonly occurring thermoacoustic vibrations are significantly reduced.
  • At least one further fuel outlet opening 8 is provided at the burner tip 7 of the burner lance 6 through the liquid fuel axially to the Burner axis A is discharged.
  • a preferably annular air outlet opening 9 is provided around the outlet opening 8 at the burner tip 7, through which the diessigbrennstoffaustrag is surrounded in the burner chamber by a preferably conically spreading air vortex flow.
  • the liquid lance discharge through the burner lance 6 into the swirl chamber 2 leads to a central fuel enrichment within the vortex-shaped fuel-air mixture, whereby the flame front forming inside the combustion chamber (not shown) is additionally stabilized and the firing temperature is increased.
  • the fuel input be it through the fuel outlet openings 4, 5 or 8 individually made coordinated with each other.
  • the burner concept according to the invention opens up a high variability of control measures due to the large number of different, separately controllable fuel feeds in the presence of an aerodynamically stabilizing burner lance, which affects both the fuel type, fuel quantity and the spatial distribution of the fuel supply within the swirl generator.

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

Claims (13)

  1. Brûleur, composé essentiellement d'un générateur de tourbillons (3) pour un flux d'air de combustion, avec une chambre à tourbillons (2) de forme conique et des moyens d'introduction de combustible dans le flux d'air de combustion, le générateur de tourbillons (3) présentant des orifices d'entrée d'air de combustion pour le flux d'air de combustion entrant tangentiellement dans la chambre à tourbillons (2) de forme conique, et les moyens d'introduction de combustible dans le flux d'air de combustion comprenant une première amenée de combustible avec un premier groupe (4) d'orifices de sortie de combustible disposés essentiellement en direction de l'axe de brûleur pour une première quantité de combustible de pré-mélange,
    caractérisé en ce que le brûleur présente au moins une deuxième amenée de combustible, avec au moins un deuxième groupe (5) d'orifices de sortie de combustible disposés essentiellement en direction de l'axe de brûleur pour une deuxième quantité de combustible de pré-mélange, qui peut être alimentée en combustible indépendamment de la première amenée de combustible,
    en ce que, le long d'un axe de brûleur (A), une lance de brûleur (6) dépasse vers l'intérieur de la chambre à tourbillons (2) à partir des côtés de la chambre à tourbillons (2) ayant la plus petite section transversale de chambre à tourbillons de telle sorte qu'elle s'étend jusqu'à au moins 50 % de la longueur de la chambre à tourbillons (29) entourée par le générateur de tourbillons le long de l'axe de brûleur, et
    en ce que les moyens d'introduction de combustible dans le flux d'air de combustion présentent également au moins un orifice de sortie de combustible (8) à l'intérieur de la lance de brûleur (6) à travers laquelle le combustible peut être extrait le long de l'axe de brûleur.
  2. Brûleur selon la revendication 1,
    caractérisé en ce que les orifices de sortie de combustible d'au moins un des deux groupes (4, 5) sont répartis sur la totalité de l'étendue axiale des orifices d'entrée d'air de combustion, et les orifices de sortie de combustible de l'autre groupe sont répartis sur une zone partielle axiale des orifices d'entrée d'air de combustion.
  3. Brûleur selon la revendication 1 ou 2,
    caractérisé en ce que les orifices de sortie de combustible d'au moins un des groupes (4, 5) sont répartis sur une première zone partielle axiale des orifices d'entrée d'air de combustion, et les orifices de sortie de combustible de l'autre groupe sont répartis sur d'autres zones partielles axiales des orifices d'entrée d'air de combustion (4).
  4. Brûleur selon la revendication 3,
    caractérisé en ce que les zones partielles axiales ne se chevauchent pas.
  5. Brûleur selon la revendication 3,
    caractérisé en ce qu'au moins deux des zones partielles axiales se chevauchent au moins partiellement.
  6. Brûleur selon l'une des revendications 1 à 5,
    caractérisé en ce que les orifices de sortie de combustible des groupes (4, 5) présentent des sections transversales de passage différentes.
  7. Brûleur selon l'une des revendications 1 à 6,
    caractérisé en ce qu'au moins un des deux groupes (4, 5) d'orifices de sortie de combustible est disposé dans la zone d'au moins un des orifices d'entrée d'air de combustion.
  8. Brûleur selon l'une des revendications 1 à 7,
    caractérisé en ce que les orifices d'entrée d'air de combustion sont des fentes d'entrée tangentielles placées essentiellement en direction de l'axe de brûleur (A).
  9. Brûleur selon la revendication 8,
    caractérisé en ce que les deux groupes d'orifices de sortie de combustible sont disposés le long des fentes d'entrée.
  10. Brûleur selon l'une des revendications 1 à 9,
    caractérisé en ce que la lance de brûleur (6) présente une pointe de lance de brûleur (7) dépassant librement dans l'espace de tourbillon (29), avec un contour arrondi.
  11. Brûleur selon la revendication 10,
    caractérisé en ce que, à la pointe de lance de brûleur (7), il est prévu l'orifice de sortie de combustible à travers lequel du combustible peut être extrait le long de l'axe de brûleur (A).
  12. Brûleur selon la revendication 11,
    caractérisé en ce que, à la pointe de lance de brûleur (7), il est prévu un orifice annulaire ou un dispositif d'orifice (9) qui entoure l'orifice de sortie de combustion et à travers lequel de l'air de combustion peut être extrait le long de l'axe de brûleur (A) de telle sorte que l'extraction de combustible à travers l'orifice de sortie de combustible est entourée de l'air de combustion.
  13. Brûleur selon l'une des revendications 1 à 12,
    caractérisé en ce que la lance de brûleur (6) présente un contour de section transversale extérieur rond stabilisant de façon aérodynamique le flux d'air de combustion à l'intérieur de la chambre à tourbillons (2).
EP04104099.9A 2003-09-01 2004-08-26 Brûleur avec lance et alimentation étagée en carburant Not-in-force EP1510755B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH14932003 2003-09-01
CH14932003 2003-09-01

Publications (2)

Publication Number Publication Date
EP1510755A1 EP1510755A1 (fr) 2005-03-02
EP1510755B1 true EP1510755B1 (fr) 2016-09-28

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EP04104099.9A Not-in-force EP1510755B1 (fr) 2003-09-01 2004-08-26 Brûleur avec lance et alimentation étagée en carburant

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US (1) US7445445B2 (fr)
EP (1) EP1510755B1 (fr)

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CN101243287B (zh) * 2004-12-23 2013-03-27 阿尔斯托姆科技有限公司 具有混合段的预混燃烧器
GB2434437B (en) 2006-01-19 2011-01-26 Siemens Ag Improvements in or relating to combustion apparatus
EP2058590B1 (fr) * 2007-11-09 2016-03-23 Alstom Technology Ltd Procédé de fonctionnement d'un brûleur
EP2220433B1 (fr) * 2007-11-27 2013-09-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
GB2455289B (en) 2007-12-03 2010-04-07 Siemens Ag Improvements in or relating to burners for a gas-turbine engine
US8479720B1 (en) 2008-10-16 2013-07-09 Oscar Enrique Figueroa Heating device and method
JP5462502B2 (ja) * 2009-03-06 2014-04-02 大阪瓦斯株式会社 管状火炎バーナ
US8616002B2 (en) * 2009-07-23 2013-12-31 General Electric Company Gas turbine premixing systems
US20120052451A1 (en) * 2010-08-31 2012-03-01 General Electric Company Fuel nozzle and method for swirl control
KR102002042B1 (ko) * 2012-05-29 2019-07-19 주성엔지니어링(주) 기판 처리 장치 및 기판 처리 방법
US20140209347A1 (en) 2013-01-29 2014-07-31 Tyco Electronics Corporation Cable Having a Sparse Shield
US9991023B2 (en) * 2013-01-29 2018-06-05 Creganna Unlimited Company Interconnect cable having insulated wires with a conductive coating
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

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EP0592717B1 (fr) * 1992-10-16 1998-02-25 Asea Brown Boveri Ag Brûleur opérant au gaz du type à prémélange
DE19545309A1 (de) * 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
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Publication number Publication date
US7445445B2 (en) 2008-11-04
EP1510755A1 (fr) 2005-03-02
US20050106522A1 (en) 2005-05-19

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