EP1213536B1 - Brûleur à prémélange avec brûleur pilote catalytique - Google Patents

Brûleur à prémélange avec brûleur pilote catalytique Download PDF

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Publication number
EP1213536B1
EP1213536B1 EP01128081A EP01128081A EP1213536B1 EP 1213536 B1 EP1213536 B1 EP 1213536B1 EP 01128081 A EP01128081 A EP 01128081A EP 01128081 A EP01128081 A EP 01128081A EP 1213536 B1 EP1213536 B1 EP 1213536B1
Authority
EP
European Patent Office
Prior art keywords
premix burner
fuel
pilot
combustion chamber
catalyst unit
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.)
Expired - Lifetime
Application number
EP01128081A
Other languages
German (de)
English (en)
Other versions
EP1213536A3 (fr
EP1213536A2 (fr
Inventor
Christian Dr. Steinbach
Timothy Dr. Griffin
Peter Dr. Jansohn
Thomas Ruck
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 EP1213536A2 publication Critical patent/EP1213536A2/fr
Publication of EP1213536A3 publication Critical patent/EP1213536A3/fr
Application granted granted Critical
Publication of EP1213536B1 publication Critical patent/EP1213536B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/28—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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
    • 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
    • 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
    • F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel

Definitions

  • the invention relates to a premix burner arrangement with a pilot fuel feed for operating a combustion chamber of a gas turbine arrangement, comprising a premix burner housing in which at least one fuel addition unit and supply air openings are provided such that gaseous and / or liquid fuel with combustion air can be mixed within the premix burner housing and a fuel Air mixture form, the downstream of the premix burner housing in the direction of the combustion chamber, which is arranged downstream of the premix burner assembly, and within the combustion chamber in the form of a spatially largely stationary forming flame to ignition can be brought.
  • a premix burner of the aforementioned type is the subject of German patent application DE 196 54 009 A1.
  • the known premix burner has a conically widening housing within which forms a fuel / air mixture by appropriate provision of air inlet slots. Further, a swirl generator is provided downstream of which gives the fuel / air mixture after passing through the premix burner a certain critical swirl number, which is required for a spatially stable flame, which forms within the combustion chamber after ignition of the fuel / air mixture. To start or ignite such Vormischbrenner it requires a targeted pilot gas supply in the premix burner.
  • a diffusion flame forms, which serves to ignite the axially in the premix burner forming fuel / air mixture, which forms an ideally spatially stable flame front near the return flow within the burner chamber.
  • the pilot gas supply serves to increase the flame stability in the lower part load range of the premix burner so in operating conditions in which the premix burner is run with lean mixtures.
  • Vormischbrennersysteme applies the resulting during combustion exhaust gas values, and in particular the NO x emissions, but worsen significantly by way of additional piloting and thereby forming the diffusion flame by increasing flame temperatures.
  • premix burners with a downstream mixing section have become known, as they emerge, for example, from EP 0 83 105 A2.
  • the premix burner downstream mixing section the fuel / air mixture is able to completely mix before the mixture enters the combustion chamber for ignition.
  • the additional pilot gas feed has a lasting effect on the NO x emissions resulting from combustion, despite the additional mixing section.
  • EP 0 909 921 A1 in which a premix burner with downstream mixing section is described, at the end of which a pilot fuel feed unit surrounding the mixing tube is provided at the end before it enters the combustion chamber.
  • the invention has for its object to provide a premix burner arrangement with a pilot fuel feed for operating a combustion chamber in a gas turbine arrangement, with a premix burner in which at least one fuel addition unit and supply air openings are provided such that gaseous and / or liquid fuel with combustion air are miscible within the premix burner and a Form fuel / air mixture, the downstream of the premix burner in the direction of the combustion chamber, which is the Vormischbrenneranssen exits, and within the combustion chamber in the form of a spatially largely stationary forming flame can be brought to ignition in such a way that on the one hand, the resulting during combustion NO x emission should be reduced significantly, on the other hand, the stability of the forming within the combustion chamber flame should be maintained or optimized.
  • the structural measures necessary for this purpose should be retrofittable as inexpensively as possible and also in premix burner arrangements already in operation.
  • a premix burner arrangement with a pilot fuel feed for operating a combustion chamber of a gas turbine arrangement is designed such that the premix burner provides a conical premix burner housing with swirl generator and comprises a mixing tube which connects downstream of the swirl generator and is connected downstream with the combustion chamber, and a catalyst unit is provided outside the premix burner, through which the pilot fuel feed takes place in such a way that a pilot fuel-air mixture flows through the catalyst unit and at least partially through it catalytically convertible and flows as a flame-stabilizing material flow into the combustion chamber.
  • premix burner refers to a premix burner assembly that flows from a conically shaped premix burner housing containing at least one fuel injection device and supply air through the supply air to form a fuel-air mixture within the premix burner housing, downstream of the premix burner housing subsequent swirl generator and optionally composed of a subsequent to the swirl generator mixing section.
  • the inventive idea departs from the known pilot gas supply within the premix burner, for example using a pilot gas lance, and generally provides catalytic conversion of a pilot fuel even before it enters the area of the combustion chamber. Due to the at least partially catalytic conversion of the supplied pilot fuel, which mixes before entering the catalyst unit with air and flows through the catalyst unit in the form of a pilot fuel / air mixture, at least a large proportion of the pilot fuel is thermally and / or catalytically reacted, creating a in the Combustion entering material flow is formed, which is designed as an ignitable gas mixture or as a kind of hot gas stream.
  • the formed in the form of an ignitable gas mixture material flow then passes directly into the region of the flame front within the combustion chamber whereby it is made to ignite and generates only minimal NO x emissions. Even in the case of a complete chemical reaction of the pilot fuel, which leads, for example, to a stream of hot gas formed, preferably consisting of the Volloxidations occur CO 2 and H 2 , only very small proportions of NO x .
  • the catalyst unit is preferably arranged downstream of the premix burner immediately before entry into the combustion chamber or downstream of the mixing section connected downstream of the swirl generator such that the catalyst unit at least partially surrounds the mixing section in a circular manner. It has proven to be particularly advantageous in the case of a catalyst unit arranged circularly around the mixing section that the catalytically converted material stream flowing into the combustion chamber from the catalyst unit is able to decisively stabilize the flame front forming within the combustion chamber in the region of the backflow zone.
  • the catalytically reacted material flow preferably meets the edge areas on the paraboloid-like flame front forming within the combustion chamber, which, as confirmed by experiments, can increase the stability of the flame. This is especially true when operating with lean fuel / air mixtures, as is the case in the lower part load range.
  • FIG. 1 shows a longitudinal section through a premix burner arrangement with a cone-shaped premix burner housing 1, in which a fuel addition unit 2, for example in the form of a spray nozzle via which liquid fuel can be atomized, is provided.
  • a fuel addition unit 2 for example in the form of a spray nozzle via which liquid fuel can be atomized
  • Via supply air openings 3 along the premix burner housing 1 incoming air enters the interior of the premix burner, in which in the presence of swirl-generating means 3 ', the so-called swirl generator, a fuel / air mixture is formed, which passes downstream of the mixing tube 4 for complete mixing.
  • the combustion chamber 5 Downstream of the mixing tube 4, the combustion chamber 5 is provided, within which forms a stable flame front 7 within the remindströmzone 8 in a conventional manner.
  • the mixing tube 4 circularly completely surrounding catalyst unit 6 is provided.
  • the catalyst unit 6 is formed from a cylinder jacket 9 which completely surrounds the mixing tube 4 at its end facing the combustion chamber 5 and which encloses a volume delimited by the outer wall of the mixing tube 4, in the region of which catalyst material 10 is provided facing the combustion chamber 5.
  • the catalyst 10 immediately downstream adjoins the combustion chamber 5, so that a flow of material permeating the catalyst 10 can open directly into the combustion chamber 5 (see arrow illustration).
  • the catalyst 10 upstream of the catalyst unit 6 upstream of a mixing region 11 is provided, within which supplied pilot fuel can completely mix with air.
  • the supply of pilot fuel preferably in gaseous form, for example. Buthan or methane, via a, incorporated within the mixing tube 4 pilot fuel supply line 12, which is provided immediately before entering the mixing section 11 of the catalyst unit 6.
  • the pilot fuel enters the premixing section 11 of the catalyst unit and flows through the catalyst 10 as a pilot fuel / air mixture.
  • the catalyst 10 Within the catalytic converter 10, at least Catalytically and / or thermally converted parts of the pilot fuel, so that after passing through the catalyst unit 10, a preferably designed as an ignitable gas mixture material flow 14 opens into the combustion chamber 5.
  • the stream 14 impinges in edge regions on the flame front 7, in which the stream 14 is able to contribute significantly to stabilize the flame front.
  • FIG. 2 shows an alternative embodiment for pilot fuel feed for a premix burner arrangement according to FIG. Similar to the exemplary embodiment of FIG. 1, the premix burner arrangement shown in FIG. 2 has a cone-shaped premix burner 1, which is connected downstream with a mixing tube 4, which in turn adjoins a combustion chamber (not shown) downstream.
  • an outer housing 15 Arranged around the mixing tube 4 is an outer housing 15 that completely surrounds the mixing tube in a circular manner and that encloses a pilot fuel feed line 12.
  • the outer housing 15 encloses with the mixing tube 4 an intermediate gap 16, via which supply air can flow into a mixing section 11 formed as a Venturi tube.
  • pilot fuel enters the mixing section 11 and is mixed with the supply air to form a pilot fuel / air mixture.
  • the mixture passes through the catalyst 10, in which the pilot fuel is at least partially reacted thermally and / or catalytically and enters the combustion chamber 5 as a preferably ignitable gas mixture.
  • the measure according to the invention of the catalytic piloting immediately before entry into the combustion chamber makes it possible, on the one hand, to decisively reduce the increases in NO x emission values usually associated with pilot gas feeds, and on the other hand, the pilot gas feed flowing into the combustion chamber in the edge regions of the flame front is able to ignite the flame to stabilize crucial, especially in critical load ranges of the gas turbine plant.

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

Claims (10)

  1. Système de brûleur à prémélange avec une alimentation en combustible pilote pour le fonctionnement d'une chambre de combustion (5) d'un système de turbine à gaz, comprenant un brûleur à prémélange dans lequel sont prévues au moins une unité d'apport de combustible (2) et des ouvertures d'amenée d'air (3) de telle sorte que du combustible gazeux et/ou liquide puisse être mélangé à l'air d'amenée comburant à l'intérieur du brûleur à prémélange (1) et forme un mélange air-combustible, qui sort du brûleur à prémélange en aval dans la direction de la chambre de combustion (5) qui est placée après le brûleur à prémélange et qui peut être enflammé à l'intérieur de la chambre de combustion (5) sous forme d'une flamme se formant de manière spatiale essentiellement stationnaire, le brûleur à prémélange présentant un boîtier de brûleur à prémélange (1) réalisé avec une forme conique avec un générateur de tourbillon (3') et comprenant aussi un tube de mélange (4), qui se raccorde en aval au générateur de tourbillon (3') et qui est connecté en aval à la chambre de combustion (5), et une unité de catalyseur (6) étant prévue en dehors du brûleur à prémélange, à travers laquelle a lieu l'alimentation en combustible pilote de telle sorte qu'un mélange air-combustible pilote traverse l'unité de catalyseur (6) et puisse être converti catalytiquement au moins en partie dans l'unité de catalyseur (6) et afflue sous forme d'un courant de matière stabilisant la flamme dans la chambre de combustion (5).
  2. Système de brûleur à prémélange selon la revendication 1,
    caractérisé en ce que l'unité de catalyseur (6) entoure circulairement au moins en partie le brûleur à prémélange en aval de sa sortie avant l'entrée dans la chambre de combustion (5).
  3. Système de brûleur à prémélange selon la revendication 1 ou 2, caractérisé en ce que pour l'alimentation en combustible pilote, on prévoit une conduite d'amenée de combustible pilote (12) ainsi qu'un dispositif de pulvérisation de combustible pilote (13), qui introduit le combustible pilote dans la section de mélange (11), dans laquelle le combustible pilote introduit peut être mélangé avec l'air amené et qui forment le mélange air-combustible pilote circulant à travers l'unité de catalyseur (6).
  4. Système de brûleur à prémélange selon l'une quelconque des revendications 1 à 3, caractérisé en ce que le courant de matière sortant de l'unité de catalyseur (6) débouche à proximité immédiate du mélange air-combustible sortant du brûleur à prémélange dans la chambre de combustion (5).
  5. Système de brûleur à prémélange selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le courant de matière sortant de l'unité de catalyseur (6) entoure circulairement complètement le mélange air-combustible sortant du brûleur à prémélange et entre dans la chambre de combustion (5).
  6. Système de brûleur à prémélange selon l'une quelconque des revendications 3 à 5, caractérisé en ce que la conduite d'amenée de combustible (12), le dispositif de pulvérisation de combustible pilote (13), la section de mélange (11) ainsi que l'unité de catalyseur (6) sont disposés circulairement autour du brûleur à prémélange et sont limités unilatéralement par celui-ci.
  7. Système de brûleur à prémélange selon l'une quelconque des revendications 1 à 6, caractérisé en ce que le boîtier de brûleur à prémélange (1) de forme conique, le générateur de tourbillon (3') et le tube de mélange (4) sont réalisés sous forme de composants séparés.
  8. Système de brûleur à prémélange selon l'une quelconque des revendications 1 à 7, caractérisé en ce que l'unité de catalyseur (6) est prévue dans la région de l'extrémité opposée au courant du tube de mélange (4).
  9. Système de brûleur à prémélange selon l'une quelconque des revendications 1 à 8, caractérisé en ce que le combustible pilote est gazeux.
  10. Système de brûleur à prémélange selon l'une quelconque des revendications 1 à 9, caractérisé en ce que le courant de matière sortant de l'unité de catalyseur (6) est un mélange gazeux inflammable.
EP01128081A 2000-12-11 2001-11-27 Brûleur à prémélange avec brûleur pilote catalytique Expired - Lifetime EP1213536B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10061526 2000-12-11
DE10061526A DE10061526A1 (de) 2000-12-11 2000-12-11 Vormischbrenneranordnung zum Betrieb einer Brennkammer

Publications (3)

Publication Number Publication Date
EP1213536A2 EP1213536A2 (fr) 2002-06-12
EP1213536A3 EP1213536A3 (fr) 2002-10-23
EP1213536B1 true EP1213536B1 (fr) 2006-09-06

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EP01128081A Expired - Lifetime EP1213536B1 (fr) 2000-12-11 2001-11-27 Brûleur à prémélange avec brûleur pilote catalytique

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US (1) US6679061B2 (fr)
EP (1) EP1213536B1 (fr)
DE (2) DE10061526A1 (fr)

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WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
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
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GB2429516B (en) * 2005-08-27 2010-12-29 Siemens Ind Turbomachinery Ltd An apparatus for modifying the content of a gaseous fuel
FR2899956B1 (fr) * 2006-04-14 2008-07-25 Thirode Grandes Cuisines Poligny Bruleur a gaz pour four de cuisine
US8124289B2 (en) * 2007-01-22 2012-02-28 Rolls-Royce Fuel Cell Systems (Us) Inc. Multistage combustor and method for starting a fuel cell system
EP2058590B1 (fr) * 2007-11-09 2016-03-23 Alstom Technology Ltd Procédé de fonctionnement d'un brûleur
WO2009068425A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
WO2009068427A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Dispositif et procédé d'utilisation d'une installation de turbine à gaz par recours à un deuxième carburant riche en hydrogène
US8220271B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Fuel lance for a gas turbine engine including outer helical grooves
US8220269B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Combustor for a gas turbine engine with effusion cooled baffle
US20100175379A1 (en) * 2009-01-09 2010-07-15 General Electric Company Pre-mix catalytic partial oxidation fuel reformer for staged and reheat gas turbine systems
US20100175386A1 (en) * 2009-01-09 2010-07-15 General Electric Company Premixed partial oxidation syngas generation and gas turbine system
US20120144832A1 (en) * 2010-12-10 2012-06-14 General Electric Company Passive air-fuel mixing prechamber
CN107228826B (zh) * 2017-06-06 2023-09-15 北京金索坤技术开发有限公司 一种用于火焰原子荧光光谱仪的双曲涡旋式传输室
EP3617599A1 (fr) * 2018-09-03 2020-03-04 Siemens Aktiengesellschaft Brûleur à mélange air-carburant amélioré
US11692711B2 (en) * 2021-08-13 2023-07-04 General Electric Company Pilot burner for combustor

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Also Published As

Publication number Publication date
EP1213536A3 (fr) 2002-10-23
DE50110931D1 (de) 2006-10-19
US6679061B2 (en) 2004-01-20
EP1213536A2 (fr) 2002-06-12
US20020189257A1 (en) 2002-12-19
DE10061526A1 (de) 2002-06-20

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