EP1213536A2 - Brûleur à prémélange avec brûleur pilote catalytique - Google Patents

Brûleur à prémélange avec brûleur pilote catalytique Download PDF

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Publication number
EP1213536A2
EP1213536A2 EP01128081A EP01128081A EP1213536A2 EP 1213536 A2 EP1213536 A2 EP 1213536A2 EP 01128081 A EP01128081 A EP 01128081A EP 01128081 A EP01128081 A EP 01128081A EP 1213536 A2 EP1213536 A2 EP 1213536A2
Authority
EP
European Patent Office
Prior art keywords
premix burner
combustion chamber
fuel
pilot fuel
air mixture
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
EP01128081A
Other languages
German (de)
English (en)
Other versions
EP1213536B1 (fr
EP1213536A3 (fr
Inventor
Christian Dr. Steinbach
Timothy Dr. Griffin
Peter Dr. Jansohn
Thoams 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
Alstom Power NV
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, Alstom Power NV 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 and to a Method for operating such a pilot fuel feed for Operation of a combustion chamber of a gas turbine arrangement, with a Premix burner housing in which at least one fuel addition unit and Supply air openings are provided such that they are more gaseous and / or more liquid Fuel with combustion air inside the premix burner housing are miscible and form a fuel-air mixture that from the Premix burner housing downstream towards the combustion chamber, which the Pre-mix burner assembly is downstream, exits and within the Combustion chamber in the form of a spatially largely stationary one Flame can be brought to ignition.
  • a premix burner of the aforementioned type is the subject of German patent application DE 196 54 009 A1.
  • the well-known premix burner has a conically widening housing within which through appropriate provision of air inlet slots a fuel / air mixture formed.
  • a swirl generator is provided downstream, which is the fuel / air mixture after passing the premix burner, a certain critical Gives swirl number, which is required for a spatially stable flame, the inside the combustion chamber after igniting the fuel / air mixture formed. To start or ignite such premix burners it is necessary a targeted pilot gas supply in the premix burner.
  • pilot gas fed into the premix burner forms a diffusion flame which for igniting the fuel / air mixture that forms axially in the premix burner serves that ideally spatially within the burner chamber forms a stable flame front near the backflow zone.
  • the pilot gas supply also serves to increase the flame stability in the lower part load range of the Premix burner in operating states in which the premix burner lean mixtures is driven.
  • Premix burners with a downstream mixing section have become known, inter alia for reasons of reduction of NO x emissions, as can be seen, for example, from EP 0 83 105 A2.
  • the fuel / air mixture is able to mix completely within the mixing section downstream of the premix burner before the mixture reaches the combustion chamber for ignition.
  • burner systems optimized in this way for starting up and also in operating states with only a lean mixture supply require piloting which is known per se, as is used in particular in the lower part-load operation of gas turbine systems.
  • the additional pilot gas supply has a lasting effect on the NO x emissions caused by the combustion, despite the additional mixing section.
  • the invention is based on the object of 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 in such a way that gaseous and / or liquid fuel can be mixed and mixed with combustion supply air within the premix burner Form a fuel / air mixture that emerges from the premix burner downstream in the direction of the combustion chamber, which is arranged downstream of the premix burner arrangement, and can be ignited within the combustion chamber in the form of a flame that is largely spatially stationary, so that, on the one hand, those that occur during combustion NO x emission values are to be decisively reduced, on the other hand the stability of the flame forming within the combustion chamber is to be further maintained or optimized.
  • the design measures required for this should be as cost-effective as possible and can also be retrofitted to premix burner arrangements which are already in operation.
  • a premix burner arrangement with a Pilot fuel feed for operating a combustion chamber Gas turbine arrangement designed in accordance with the preamble of claim 1, that a catalyst unit is provided outside the premix burner by through which the pilot fuel is fed in such a way that a pilot fuel-air mixture flows through and at least partially in the catalyst unit is catalytically implementable and as a flame stabilizing material flow into the Combustion chamber flows in.
  • premix burner refers to a premix burner arrangement that is made up of a preferably conical premix burner housing in which contain at least one fuel injection device and supply air openings are, through the supply air to form a fuel-air mixture inside the
  • the premix burner housing flows to the premix burner housing downstream swirl generator as well as optionally from a Swirl generator subsequent mixing section is composed.
  • the idea according to the invention moves away from the pilot gas supply known per se within the premix burner, for example using a pilot gas lance, and basically provides for a catalytic conversion of a pilot fuel even before it reaches the area of the combustion chamber. Due to the at least partial catalytic conversion of the supplied pilot fuel, which mixes with air before entering the catalyst unit 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 converted, as a result of which a Combustion chamber entering material flow is formed, which is designed as an ignitable gas mixture or as a kind of hot gas flow.
  • the material flow which is in the form of an ignitable gas mixture, then arrives directly in the area of the flame front within the combustion chamber, causing it to ignite and producing only minimal NO x emissions. Even in the case of a complete chemical conversion of the pilot fuel, which leads, for example, to a material flow in the form of a hot gas, preferably consisting of the full oxidation products CO 2 and H 2 , only minimal amounts of NO x are produced .
  • the catalyst unit is preferably immediately downstream of the premix burner Entry into the combustion chamber or downstream of the swirl generator Mixing section arranged such that the catalyst unit the mixing section at least partially surrounds circularly. It has proven to be particularly advantageous for one circularly arranged around the mixing section catalyst unit found that the catalytically converted flowing from the catalyst unit into the combustion chamber Material flow within the combustion chamber in the area of the backflow zone forming flame front can stabilize decisively.
  • the catalytic converted material flow preferably meets in marginal areas within of the combustion chamber paraboloid-like flame front, whereby how Experiments confirm that the stability of the flame can be increased. This is especially true when operating with lean fuel / air mixtures, such as the one below Partial load range is the case.
  • Figure 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 an atomizer nozzle, via the Liquid fuel can be atomized, is provided.
  • a Fuel addition unit 2 for example in the form of an atomizer nozzle, via the Liquid fuel can be atomized, is provided.
  • incoming air enters the interior of the Premix burner, in which in the presence of swirl-generating agents 3 ', the so-called swirl generator, a fuel / air mixture is formed which for Complete mixing flows downstream into the mixing tube 4.
  • the combustion chamber 5 Downstream of the Mixing tube 4, the combustion chamber 5 is provided, within itself a stable flame front 7 within the backflow zone 8 formed.
  • the catalyst unit 6 is made of one, the mixing tube 4 on its combustion chamber 5 facing end completely formed cylinder jacket 9, the one encloses limited volume with the outer wall of the mixing tube 4, in whose the catalyst material 10 facing the combustion chamber 5 is provided.
  • the catalyst 10 adjoins the combustion chamber 5 downstream, so that a material flow penetrating the catalyst 10 directly into the combustion chamber 5 (see arrow display) can open.
  • the catalyst 10 within the A mixing area 11 is provided upstream of the catalyst unit 6, Mix completely with air within the supplied pilot fuel can.
  • the supply of pilot fuel preferably in gaseous form, for example. Butane or methane takes place via an integrated inside the mixing tube 4 Pilot fuel supply line 12, the immediately before entering the mixing section 11 of the Catalyst unit 6 is provided.
  • the pilot fuel enters the Premixing section 11 of the catalyst unit and flows through as a pilot fuel / air mixture the catalyst 10. At least within the catalyst 10 Parts of the pilot fuel are converted catalytically and / or thermally, so that after Passing through the catalyst unit 10 preferably as an ignitable Gas mixture formed material stream 14 opens into the combustion chamber 5.
  • the Material flow 14 meets in edge areas on the flame front 7, in which the material flow 14 can contribute significantly to the stabilization of the flame front.
  • FIG. 2 shows an alternative embodiment for the pilot fuel feed for a Premix burner arrangement shown in Figure 1. Similar to the Embodiment of Figure 1 has that shown in Figure 2 Premix burner arrangement a conical premix burner 1, which is connected downstream to a mixing tube 4, which in turn is connected downstream to a adjacent combustion chamber, not shown.
  • the mixing tube 4 is a circular surrounding completely the mixing tube Arranged outer housing 15, which includes a pilot fuel supply line 12.
  • the outer housing 15 includes an intermediate gap 16 with the mixing tube 4 the supply air can flow into a mixing section 11 designed 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. This occurs downstream Mixture through the catalyst 10 in which the pilot fuel is at least partially is implemented thermally and / or catalytically and as preferably ignitable Gas mixture enters the combustion chamber 5.
  • the inventive measure of catalytic piloting immediately before entering the combustion chamber makes it possible, on the one hand, to significantly reduce the increases in NO x emission values usually associated with pilot gas supplies, and on the other hand, the pilot gas supply flowing into the combustion chamber in the edge regions of the flame front is capable of the flame decisive stabilization, especially in critical load areas 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)
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 true EP1213536A2 (fr) 2002-06-12
EP1213536A3 EP1213536A3 (fr) 2002-10-23
EP1213536B1 EP1213536B1 (fr) 2006-09-06

Family

ID=7666594

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01128081A Expired - Lifetime EP1213536B1 (fr) 2000-12-11 2001-11-27 Brûleur à prémélange avec brûleur pilote catalytique

Country Status (3)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009068425A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz

Families Citing this family (19)

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Publication number Priority date Publication date Assignee Title
DE10049203A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brennstoffeinleitung in einen Vormischbrenner
DE10049205A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners
US6928822B2 (en) * 2002-05-28 2005-08-16 Lytesyde, Llc Turbine engine apparatus and method
JP4913746B2 (ja) * 2004-11-30 2012-04-11 アルストム テクノロジー リミテッド 予混合バーナー内の水素を燃焼する方法及び装置
EP1828684A1 (fr) * 2004-12-23 2007-09-05 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange
US7752850B2 (en) * 2005-07-01 2010-07-13 Siemens Energy, Inc. Controlled pilot oxidizer for a gas turbine combustor
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
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
US8220269B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Combustor for a gas turbine engine with effusion cooled baffle
US8220271B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Fuel lance for a gas turbine engine including outer helical grooves
US20100175386A1 (en) * 2009-01-09 2010-07-15 General Electric Company Premixed partial oxidation syngas generation and gas turbine system
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
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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DE19654009A1 (de) 1996-12-21 1998-06-25 Asea Brown Boveri Vormischbrenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff

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Publication number Priority date Publication date Assignee Title
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009068425A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
US8033821B2 (en) 2007-11-27 2011-10-11 Alstom Technology Ltd. Premix burner for a gas turbine

Also Published As

Publication number Publication date
US6679061B2 (en) 2004-01-20
EP1213536B1 (fr) 2006-09-06
DE50110931D1 (de) 2006-10-19
US20020189257A1 (en) 2002-12-19
DE10061526A1 (de) 2002-06-20
EP1213536A3 (fr) 2002-10-23

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