EP1645802A2 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

Info

Publication number
EP1645802A2
EP1645802A2 EP05108942A EP05108942A EP1645802A2 EP 1645802 A2 EP1645802 A2 EP 1645802A2 EP 05108942 A EP05108942 A EP 05108942A EP 05108942 A EP05108942 A EP 05108942A EP 1645802 A2 EP1645802 A2 EP 1645802A2
Authority
EP
European Patent Office
Prior art keywords
fuel
premix burner
injection
swirl
lance
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
EP05108942A
Other languages
German (de)
English (en)
Other versions
EP1645802B1 (fr
EP1645802A3 (fr
Inventor
Stefano Bernero
Christian Jörg Motz
Christian Oliver Paschereit
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.)
GE Vernova 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 EP1645802A2 publication Critical patent/EP1645802A2/fr
Publication of EP1645802A3 publication Critical patent/EP1645802A3/fr
Application granted granted Critical
Publication of EP1645802B1 publication Critical patent/EP1645802B1/fr
Anticipated expiration legal-status Critical
Not-in-force 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
    • F23R3/286—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
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately 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
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a burner according to the preamble of the first claim.
  • Premix burners operated according to the concept of lean premix combustion have low pollutant emissions, but also a clearly limited stability and operating range.
  • thermoacoustic vibrations lead to these restrictions.
  • the extension of the stability range takes place during the conventional operation of a premix burner with a pilot injection, which is used in particular in the lower load range.
  • Even small amounts of e.g. However, 10% pilot gas can lead to significantly higher pollutant emissions, since the pilot flames operate in diffusion mode. In the upper load range, the pilot injection is switched off or reduced as far as possible to ensure low pollutant emissions.
  • this pilot burner is realized by injecting fuel in the center of the swirl body, here called a double cone.
  • the gas flowing into the interior of the double-cone burner burns in a flame which is deeply stabilized in the interior of the burner.
  • a burner with stepped premix gas injection is known in which a fuel lance protrudes into the swirl body.
  • the fuel supply can be controlled so that outlet openings in the fuel lance and outlet openings on the swirler can be fed independently with premixed gas.
  • the outlet openings on the swirl body and on the lance can be arranged in such a way that no outlet openings are arranged on the swirl body arranged opposite the swirl body at the outlet openings arranged on the lance.
  • the invention has for its object to ensure in a burner of the type mentioned, over the entire load range optimal injection of the fuel and to suppress thermoacoustic oscillations even more effective.
  • the essence of the invention is to achieve a stepped injection of the fuel into the combustion air by arranging a fuel lance projecting into the swirl space, whereby a part of the fuel injection means in the combustion air inlet slots is replaced by fuel injection means on the fuel lance.
  • the advantages of the invention can be seen in the fact that optimum injection of the fuel is ensured over the entire load range. Due to the stepped injection via the lance and the additional injection openings, the operating range of premix burners can be extended. The operation of these fuel staging premix burners covers at least the entire operating range of conventional pilot / premix burners.
  • an asymmetric injection of the fuel pulsations can be prevented even more effective.
  • the asymmetry refers to opposite in the flow direction pairs of injection ports and the injection openings in the lance.
  • the asymmetry can be done statically by no injection opening is arranged in the opposite region of a Eindüsungsö réelle. However, this can also be done by an individual control of the fuel supply to the symmetrically present fuel injection openings or by rotating the lance.
  • Opposing Brennstoffindüsungsötechnischen are then supplied by the control of different amounts of fuel and thus achieved depending on the load point or start or Abfahr discipline a symmetrical or asymmetric fuel profile in the swirl chamber of the swirl generator.
  • a graded fuel injection allows an optimal driving with respect to an adaptation to the fuel composition, since different fuels or mixtures, for example, have a different penetration depth.
  • the burner according to FIG. 1 consists of a swirl generator 30 which essentially consists of two half-hollow partial cone bodies 1, 2 which are offset from one another. Such a burner is referred to as a double-cone burner.
  • a swirl generator 30 which essentially consists of two half-hollow partial cone bodies 1, 2 which are offset from one another.
  • Such a burner is referred to as a double-cone burner.
  • the displacement of the respective central axis 1 b, 2 b of the partial cone bodies 1, 2 to each other on both sides in a mirror-image arrangement creates a respective tangential air inlet slot 19, 20, (Fig. 2-4), through which the combustion air 15 into the interior of the burner, ie in the conical cavity 14, also called swirl space, flows.
  • the two partial cone bodies 1, 2 each have a cylindrical initial part 1a, 2a, which also analogously to the partial cone bodies 1, 2 offset from each other, so that the tangential air inlet slots 19, 20 are present from the beginning.
  • a fuel lance 3 is arranged, which projects downstream into the swirl chamber 14.
  • Both partial cone bodies 1, 2 each have a fuel line 8, 9, which are provided with openings 17 through which the gaseous fuel 13, which is mixed by the tangential air inlet slots 19, 20 flowing combustion air 15. The position of these fuel lines 8, 9 is schematically shown in Fig. 2-4.
  • the fuel lines 8, 9 are attached to the end of the tangential air inlet slots 19, 20, so that there takes place the admixture 16 of the gaseous fuel 13 with the incoming combustion air 15.
  • the burner at the burner outlet 29 a collar-shaped, as an anchor for the part cone body 1, 2 serving end plate 10 with a number of holes 11, through which dilution air or cooling air 18 the front part of the combustion chamber of the combustion chamber 22 and whose wall can be supplied. Ignition takes place at the top of the return flow zone 6. Only at this point can a stable flame front 7 arise. A flashback of the flame into the interior of the burner, as is latent in premixing lines, is less here.
  • the fuel lance 3 has openings 5, by means of which gaseous fuel can be injected into the swirl chamber 14 of the swirl generator.
  • a fuel injection 4 may be arranged, which may be, for example, an air-assisted nozzle or a pressure atomizer. By means of this fuel injection 4, additional liquid fuel can be injected.
  • the lance 3 can also be subdivided into a plurality of regions so that individual injection of fuel can take place in these regions.
  • Fig. 2 - 4 is also the position of the baffles 21 a, 21 b shown. They have flow initiation functions, wherein they extend, differently long, the respective end of the partial cone bodies 1 and 2 in the direction of flow of the combustion air 15.
  • the channeling of the combustion air into the conical cavity 14 can be optimized by opening or closing the baffles 21 a, 21 b about the pivot point 23.
  • the swirl generator 30 consisting of the partial cone body 1 with the fuel line 8 and the partial cone body 2 with the fuel line 9 on the left side in the operating position and on the right side in a comparison position to compare the configuration of the two partial cone body shown ,
  • the openings 17a of the fuel line 8 are arranged asymmetrically with respect to the openings 17b of the fuel line 9. Fuel openings 17a are thus opposite areas of the fuel line 9, in which no fuel openings are arranged and fuel ports 17b are thus areas of the fuel line 8 opposite, in which no fuel ports are arranged. As a result, an asymmetric fuel profile is generated during the injection of the fuel into the combustion air.
  • the type and strength of the generated asymmetry must be adapted to the special case. Burner system with few pulsations may have a low asymmetry of the fuel injection, in systems with high pulsations, the asymmetry must be increased.
  • FIG. 6 schematically shows a swirl generator, as is basically known from its function from EP 0 704 657 A2, the disclosure of which is hereby incorporated by reference. According to the invention, however, the fuel injection has now been adjusted.
  • the burner shown here comprises a swirl generator 30 comprising two partial cone bodies 1, 2 and a mixing tube 50 arranged downstream, to which the combustion chamber 22 adjoins downstream.
  • the swirl chamber 14 protrudes in the downstream direction of the fuel lance 3.
  • the lance and the fuel injections 5 are arranged in the swirl space such that the fuel injection takes place in the upper part of the swirl space 14. It is not shown that further injection openings can be arranged downstream in the lance, which can be addressed, for example, via separate fuel lines.
  • the openings 17 a of the fuel line 8 and the openings 17 b of the fuel line 9 are arranged in the downstream part of the swirl chamber 14. Fuel openings 17a and 17b are thus substantially opposite areas in which no fuel openings 5 are arranged in the lance 3. Thereby, a stepped introduction of the fuel via the lines 12 and 8 and 9 are generated.
  • the injection via the openings 17a, 17b can of course also be asymmetric as described above in FIG.
  • the fuel distribution system of the external pilot fuel injection at the mixing tube 50 can be used for the fuel injection via the long lance 3.
  • FIG. 7 shows a cross section through the swirl generator from FIG. 6.
  • the swirl generator here consists of four partial cone shells 1, 1 ', 2, 2' on which in each case in the region of the air inlet slots gas injection openings 17a, 17a ', 17b, 17b' are arranged.
  • the gas outlet openings 5 of the lance are rotated at an angle ⁇ with respect to the gas injection openings 17a, 17a ', 17b, 17b'.
  • the angle ⁇ can be adjusted so that a desired asymmetry is achieved.
  • the rotation may also be 0 °, which means that there is no asymmetry, which may be advantageous for certain operating conditions.
  • the adjustment of the angle ⁇ can also take place during operation, so that the desired asymmetry can be set in each operating state.
  • this for rotation of the lance this can be rotatably supported and via a drive 51, e.g. a stepping motor, are rotated, see FIG. 6.
  • FIG. 8 shows another embodiment of the double-cone burner according to the invention.
  • the swirl space 14 is formed by the part cone shells 1 and 2.
  • the combustion air flows via the air inlet slots 19 and 20 into the swirl chamber 14.
  • fuel ports 17a and 17b are arranged, via which fuel can be injected into the combustion air.
  • the resulting fuel-air mixture is transported into the combustion chamber and ignited.
  • the double-cone burner in this example each has eight fuel injection ports 17a and 17b, which are individually supplied with fuel via a conduit.
  • a valve 31 to 38, respectively 41 to 48 are arranged, each of which can be controlled independently of the other.
  • opposing fuel injection openings 17a and 17b are now controlled by means of the valves 31 and 41, 32 and 42, 33 and 43, etc., so that at least one of the eight opposite Pairs of fuel ports have a different fuel mass flow with respect to the opposite fuel port and so asymmetric fuel supply takes place.
  • the supply of fuel to the lance via two fuel lines, in each of which a fuel valve 39 and 49 is arranged.
  • the lance is divided into a downstream part 3b and an upstream part 3a, which parts can each be independently supplied with fuel.
  • Via the valve 39, the part 3b and via the valve 49 of the part 3a is controlled. By opening the valves 39 and 49, fuel can flow out through openings 5b and 5a into the swirl space.
  • the parts 3a and 3b of the fuel lance can be rotated analogously to FIGS. 6 and 7.
  • the rotation of the parts 3a and 3b can be independent of each other, whereby a higher degree of asymmetry is possible.
  • the lance can be subdivided into other parts as described above, as described above.
  • the degree of pulsations can be determined and by means of the fuel injection ports 3a, 3b, 17a and 17b and the associated valve pairs 31 and 41, etc., and 39 and 49, the degree of asymmetry can be adapted to the circumstances.
  • this control of asymmetry may be combined with staged combustion according to the disclosure of DE 100 64 893 A1, the disclosure of which is hereby incorporated, in order to more effectively prevent harmful pulsations.
  • the external pilot fuel injection fuel distribution system can be used for fuel injection via the long lance.
  • all fuel injection stages are in operation at least under full load conditions. Also, not only partially, as described above, on the injection in a Vormischkanal, ie an air inlet slot, but completely waived The injection of fuel would then be ensured via the lance.
  • the invention is not limited to the embodiment shown and described.
  • the embodiment according to FIG. 5 can also be connected to the embodiment according to FIG. 8.
  • the active control of the valves can be minimized.
  • the number of fuel holes and thus the number of valves can be arbitrarily adapted to the requirements.
  • the burner may also have other shapes than shown in the embodiment and other types of burners may be used.
  • the burner shown can be varied as desired with respect to the shape and size of the tangential air inlets 19, 20.
  • the number of partial bodies of the swirl generator can be chosen arbitrarily.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)
EP05108942.3A 2004-10-11 2005-09-28 Brûleur à prémélange Not-in-force EP1645802B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004049491A DE102004049491A1 (de) 2004-10-11 2004-10-11 Vormischbrenner

Publications (3)

Publication Number Publication Date
EP1645802A2 true EP1645802A2 (fr) 2006-04-12
EP1645802A3 EP1645802A3 (fr) 2013-05-08
EP1645802B1 EP1645802B1 (fr) 2015-08-19

Family

ID=35539589

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05108942.3A Not-in-force EP1645802B1 (fr) 2004-10-11 2005-09-28 Brûleur à prémélange

Country Status (3)

Country Link
US (1) US7780437B2 (fr)
EP (1) EP1645802B1 (fr)
DE (1) DE102004049491A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007134580A1 (fr) * 2006-05-19 2007-11-29 Ulrich Dreizler Modélisation de flamme
EP2071156A1 (fr) 2007-12-10 2009-06-17 ALSTOM Technology Ltd Système de distribution de carburant d'une turbine à gaz avec ensemble brûleur à plusieurs étages
WO2009127240A1 (fr) * 2008-04-16 2009-10-22 Man Turbo Ag Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre
US9028247B2 (en) 2010-11-17 2015-05-12 Alstom Technology Ltd Combustion chamber and method for damping pulsations
CN111886068A (zh) * 2018-01-26 2020-11-03 唐纳森公司 用于将来自喷射器的喷雾混入气体中的混合装置、以及包括混合装置的系统

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CN101137868A (zh) * 2005-03-09 2008-03-05 阿尔斯通技术有限公司 用于产生可燃燃料/气体混合物的预混燃烧器
US8062027B2 (en) * 2005-08-11 2011-11-22 Elster Gmbh Industrial burner and method for operating an industrial burner
DE102005049245A1 (de) * 2005-10-14 2007-04-19 BSH Bosch und Siemens Hausgeräte GmbH Brenner
AU2007256045A1 (en) * 2006-06-02 2007-12-13 Mike Eggers Limited Noise generating device to scare birds or trigger avalanches
DE102006051286A1 (de) * 2006-10-26 2008-04-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennervorrichtung
US8015932B2 (en) * 2007-09-24 2011-09-13 General Electric Company Method and apparatus for operating a fuel flexible furnace to reduce pollutants in emissions
EP2208927B1 (fr) * 2009-01-15 2016-03-23 Alstom Technology Ltd Brûleur d'une turbine à gaz
EP2230455B1 (fr) * 2009-03-16 2012-04-18 Alstom Technology Ltd Brûleur pour une turbine à gaz et procédé de refroidissement local d'un flux de gaz chauds passant par un brûleur
DE102009045950A1 (de) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
EP2348256A1 (fr) * 2010-01-26 2011-07-27 Alstom Technology Ltd Procédé de fonctionnement d'une turbine à gaz et turbine à gaz
EP2423598A1 (fr) * 2010-08-25 2012-02-29 Alstom Technology Ltd Dispositif de combustion
DE102011118411A1 (de) * 2010-12-09 2012-06-14 Alstom Technology Ltd. Brennkammer und Verfahren zum Liefern von Brennstoffen an eine Brennkammer
US9016039B2 (en) * 2012-04-05 2015-04-28 General Electric Company Combustor and method for supplying fuel to a combustor
US20150316266A1 (en) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Burner with adjustable radial fuel profile
EP2940389A1 (fr) * 2014-05-02 2015-11-04 Siemens Aktiengesellschaft Agencement de brûleur de combustion
JP6602004B2 (ja) * 2014-09-29 2019-11-06 川崎重工業株式会社 燃料噴射器及びガスタービン
US10533740B2 (en) 2015-07-09 2020-01-14 Carrier Corporation Inward fired ultra low NOX insulating burner flange
DE102018205874A1 (de) * 2018-04-18 2019-10-24 Siemens Aktiengesellschaft Brenner mit selektiver Anpassung des Bohrungsmusters für die Gaseindüsung
KR102460672B1 (ko) * 2021-01-06 2022-10-27 두산에너빌리티 주식회사 연료 노즐, 연료 노즐 모듈 및 이를 포함하는 연소기

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JP2989515B2 (ja) * 1995-04-11 1999-12-13 三菱重工業株式会社 ガスタービンの予混合式燃焼装置
WO2001003550A1 (fr) * 1999-07-07 2001-01-18 Danny Morris Meuble
DE20009526U1 (de) * 2000-05-26 2000-09-21 ERC Emissions-Reduzierungs-Concepte GmbH, 22844 Norderstedt Gas-/Ölbrenner
US6769903B2 (en) * 2000-06-15 2004-08-03 Alstom Technology Ltd Method for operating a burner and burner with stepped premix gas injection
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DE10104150A1 (de) * 2001-01-30 2002-09-05 Alstom Switzerland Ltd Brenneranlage und Verfahren zu ihrem Betrieb
DE10108560A1 (de) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Verfahren zum Betrieb einer Ringbrennkammer sowie eine diesbezügliche Ringbrennkammer
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DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
DE10205839B4 (de) * 2002-02-13 2011-08-11 Alstom Technology Ltd. Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
DE10334228A1 (de) * 2002-08-19 2004-03-04 Alstom (Switzerland) Ltd. Verfahren zum Betrieb eines Vormischbrenners sowie Vorrichtung zur Durchführung des Verfahrens

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007134580A1 (fr) * 2006-05-19 2007-11-29 Ulrich Dreizler Modélisation de flamme
EP2071156A1 (fr) 2007-12-10 2009-06-17 ALSTOM Technology Ltd Système de distribution de carburant d'une turbine à gaz avec ensemble brûleur à plusieurs étages
US8776524B2 (en) 2007-12-10 2014-07-15 Alstom Technology Ltd. Fuel distribution system for a gas turbine with multistage burner arrangement
WO2009127240A1 (fr) * 2008-04-16 2009-10-22 Man Turbo Ag Procédé de fonctionnement d'un brûleur à pré-mélange et brûleur à prémélange approprié pour mettre ledit procédé en oeuvre
US10557634B2 (en) 2008-04-16 2020-02-11 Man Energy Solutions Se Method for operating a premix burner, and a premix burner for carving out the method
US9028247B2 (en) 2010-11-17 2015-05-12 Alstom Technology Ltd Combustion chamber and method for damping pulsations
CN111886068A (zh) * 2018-01-26 2020-11-03 唐纳森公司 用于将来自喷射器的喷雾混入气体中的混合装置、以及包括混合装置的系统

Also Published As

Publication number Publication date
DE102004049491A1 (de) 2006-04-20
EP1645802B1 (fr) 2015-08-19
US20060183069A1 (en) 2006-08-17
US7780437B2 (en) 2010-08-24
EP1645802A3 (fr) 2013-05-08

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