EP1217295B1 - Brûleur pour la génération d'un gaz chaud - Google Patents

Brûleur pour la génération d'un gaz chaud Download PDF

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Publication number
EP1217295B1
EP1217295B1 EP01129165A EP01129165A EP1217295B1 EP 1217295 B1 EP1217295 B1 EP 1217295B1 EP 01129165 A EP01129165 A EP 01129165A EP 01129165 A EP01129165 A EP 01129165A EP 1217295 B1 EP1217295 B1 EP 1217295B1
Authority
EP
European Patent Office
Prior art keywords
burner
outlet
combustion chamber
bodies
combustion
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
EP01129165A
Other languages
German (de)
English (en)
Other versions
EP1217295A3 (fr
EP1217295A2 (fr
Inventor
Christian Oliver Dr. Paschereit
Ephraim Prof. Dr. Gutmark
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 EP1217295A2 publication Critical patent/EP1217295A2/fr
Publication of EP1217295A3 publication Critical patent/EP1217295A3/fr
Application granted granted Critical
Publication of EP1217295B1 publication Critical patent/EP1217295B1/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
    • F23R3/286—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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • 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 present invention relates to the field of burner technology. It relates to a burner for the production of hot gases according to the preamble of claim 1.
  • thermoacoustic Vibrations pose a threat to any type of combustion application. They result in high amplitude pressure oscillations, a limitation of the operating range, and can increase pollutant emissions. This is especially true for low acoustic attenuation combustion systems. In order to allow high power conversion over a wide operating range with respect to pulsations and emissions, active control of the combustion vibrations may be necessary.
  • EP-A1-0 918 152 it is proposed to control the thermoacoustic oscillations in a combustion system by arranging means for the acoustic excitation of the working gas in the region of the burner. However, this is associated with additional equipment and control effort.
  • a similar acoustic concept (EP-A1-1 050 713) works with an active suppression by a feedback control loop with corresponding phase rotation.
  • EP-A1-0 987 495 it is proposed to additionally mix an inert gas such as N 2 , CO 2 or the like for minimizing thermoacoustic oscillations in gas turbine combustors to the fuel stream.
  • an inert gas such as N 2 , CO 2 or the like for minimizing thermoacoustic oscillations in gas turbine combustors to the fuel stream.
  • EP-A1-0 985 877 further proposes to accelerate the flow in the axial direction by minimizing thermoacoustic oscillations in gas turbine combustion chambers by nozzle-like design of the burner outlet, or nozzle-like shaped attachments are attached to the burner.
  • EP-A1-1 048 898 discloses a burner (double-cone burner) in which a plurality of internals projecting into the flow are provided in the burner cone for introducing axial vortical strength.
  • Coherent structures play a crucial role in mixing processes between air and fuel.
  • the dynamics of these structures consequently influence the combustion and thus the heat release.
  • Controlling the combustion instabilities is possible by influencing the shear layer between the fresh gas mixture and the recirculated exhaust gas (see, for example, Paschereit et al., "Structure and Control of Thermoacoustic Instabilities in a Gas-turbine Burner, Combustion, Slicing & Technology, Vol. 138, pp. 213-232 (1998)).
  • Paschereit et al. "Structure and Control of Thermoacoustic Instabilities in a Gas-turbine Burner, Combustion, Slicing & Technology, Vol. 138, pp. 213-232 (1998).
  • it makes sense to influence the formation of coherent structures by influencing the outflow boundary layer at the burner outlet.
  • thermoacoustic oscillations It is an object of the invention to provide a burner in which limited by very simple structural means thermoacoustic oscillations or can be completely suppressed.
  • the basic idea of the invention is to influence the formation of coherent structures so that the generation of high-frequency combustion-driven vibrations is prevented.
  • Coherent structures are to be understood as flow vortices that arise due to flow instabilities in the shear layers forming at the burner exit.
  • the influence of coherent structures on combustion instabilities is most pronounced when the flow instability has overlapped its highest growth rate and the vortices have reached their maximum size.
  • the axial position of the highest growth rate can be influenced inter alia by changing the thickness of the outflow boundary layer.
  • a preferred embodiment of the invention is characterized in that the means for changing the thickness of the Abströmgrenz für comprise a shear layer fence, which extends along the exit edge of the burner outlet and protrudes with its height substantially parallel to the flow direction into the combustion chamber. Due to the shear layer fence, which preferably has a height of a few millimeters, the thickness of the outflow boundary layer is increased in a particularly simple manner and thus the vortex formation in the axial direction is displaced out of the area of the flame, so that the periodic heat release associated with the vortex formation is avoided.
  • the burner is preferably designed as a double-cone burner and comprises at least two hollow, conical, nested in the flow direction part body whose center axes are offset from each other, such that adjacent walls of the body part tangential air inlet channels for the inflow of combustion air in the bounded by the partial body interior, wherein the combustion chamber side edges of the partial body form the outlet edges of the burner outlet.
  • Fig. 1 the structure of a double-cone burner is shown in the plan view from the front (contrary to the flow direction), as known for example from EP-A1-1 048 898 and is particularly suitable for the realization of the invention.
  • the burner 10 comprises two conical partial bodies 11 and 12, which are offset from one another in a central plane, such that adjacent walls of the partial bodies 11, 12 form tangential air inlet ducts for the inflow of combustion air into the interior 25 delimited by the partial bodies 11, 12.
  • Of the Interior 25 opens with a burner outlet 22 to a subsequent combustion chamber 23 (Fig. 2).
  • the combustion chamber side edges of the body parts 11, 12 form the outlet edges 16, 17 of the burner outlet 22.
  • Around the burner outlet 22 around a transverse to the flow direction extending front plate 14 is attached, which is provided with a plurality of distributed holes 15 is provided.
  • the axial position of the highest growth rate of the coherent structures can be influenced inter alia by changing the thickness of the outflow boundary layer 18. According to a preferred embodiment of the invention, this is achieved in that, according to FIG. 3, a shear layer fence 21, for example in the form of a sheet metal strip, is provided, which extends along the exit edge 16, 17 of the burner outlet 22 and with its height substantially parallel to the flow direction in FIG the combustion chamber 23 protrudes.
  • FIG. 3 shows the effect of the invention on the suppression of a pressure oscillation in the 1000 Hz range.
  • FIG. 3 shows the pressure amplitudes (Amp) measured with two transducers as a function of the thermal output (power) of a burner with shear layer fence 21 (solid circles and rectangles) and without shear layer fence (empty circles and rectangles). It is clearly evident from FIG. 3 that the occurrence of vibrations above a certain power point can be largely prevented with the aid of the shear layer fence.

Landscapes

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

Claims (4)

  1. Brûleur (10) pour la génération d'un gaz chaud, lequel brûleur (10) débouche avec une sortie de brûleur (22) bordée d'une arête de sortie (16, 17) dans une chambre de combustion (23), dans laquelle un mélange air-combustible sortant de la sortie du brûleur (22) en formant une couche limite d'efflux (18, 18') produit une flamme (20) après l'allumage du brûleur (10), caractérisé en ce que pour empêcher des diffusions périodiques de chaleur et des oscillations thermoacoustiques associées dans la chambre de combustion (23), on dispose au niveau de la sortie du brûleur (22) des moyens (21) pour modifier l'épaisseur de la couche limite d'efflux (18, 18').
  2. Brûleur selon la revendication 1, caractérisé en ce que les moyens pour modifier l'épaisseur de la couche limite d'efflux (18, 18') comprennent une barrière de couche de cisaillement (21) qui s'étend le long de l'arête de sortie (16, 17) de la sortie du brûleur (22) et qui pénètre avec sa hauteur dans la chambre de combustion (23) essentiellement parallèlement à la direction d'écoulement.
  3. Brûleur selon la revendication 2, caractérisé en ce que la hauteur de la barrière de couche de cisaillement (21) mesure quelques millimètres, de préférence environ 5 mm.
  4. Brûleur selon l'une quelconque des revendications 1 à 3, caractérisé en ce que le brûleur (10) est réalisé sous forme de brûleur à double cône, et comprend au moins deux corps partiels creux de forme conique (11, 12) qui sont décalés l'un par rapport à l'autre dans un plan médian (24), de telle sorte que des parois adjacentes des corps partiels (11, 12) forment des canaux d'entrée d'air tangentiels pour l'afflux d'air comburant dans l'espace interne (25) limité par les corps partiels (11, 12), les bords des corps partiels (11, 12) du côté de la chambre de combustion formant les arêtes de sortie (16, 17) de la sortie du brûleur (22).
EP01129165A 2000-12-23 2001-12-08 Brûleur pour la génération d'un gaz chaud Expired - Lifetime EP1217295B1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE10065206 2000-12-23
DE10065206 2000-12-23
DE10120960 2001-04-27
DE10120960 2001-04-27

Publications (3)

Publication Number Publication Date
EP1217295A2 EP1217295A2 (fr) 2002-06-26
EP1217295A3 EP1217295A3 (fr) 2002-11-20
EP1217295B1 true EP1217295B1 (fr) 2006-08-23

Family

ID=26008099

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01129165A Expired - Lifetime EP1217295B1 (fr) 2000-12-23 2001-12-08 Brûleur pour la génération d'un gaz chaud

Country Status (3)

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US (1) US6773257B2 (fr)
EP (1) EP1217295B1 (fr)
DE (1) DE50110801D1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100119984A1 (en) * 2008-11-10 2010-05-13 Fox Allen G Abatement system

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4330083A1 (de) * 1993-09-06 1995-03-09 Abb Research Ltd Verfahren zum Betrieb eines Vormischbrenners
DE19547912A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19548853A1 (de) * 1995-12-27 1997-07-03 Abb Research Ltd Kegelbrenner
US5865609A (en) * 1996-12-20 1999-02-02 United Technologies Corporation Method of combustion with low acoustics
DE19721937B4 (de) 1997-05-26 2008-12-11 Alstom Vormischbrenner zum Betrieb eines Aggregates zur Erzeugung eines Heissgases
WO1999006767A1 (fr) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Brûleur
DE19736902A1 (de) 1997-08-25 1999-03-04 Abb Research Ltd Brenner für einen Wärmeerzeuger
EP0918152A1 (fr) 1997-11-24 1999-05-26 Abb Research Ltd. Procédé et dispositif pour contrÔler les vibrations thermoacoustiques dans les chambres de combustion
DE19757189B4 (de) * 1997-12-22 2008-05-08 Alstom Verfahren zum Betrieb eines Brenners eines Wärmeerzeugers
EP0931979A1 (fr) * 1998-01-23 1999-07-28 DVGW Deutscher Verein des Gas- und Wasserfaches -Technisch-wissenschaftliche Vereinigung- Procédé et dispositif pour supprimer les fluctuations par flamme et par pression dans un four
DE19831933C1 (de) * 1998-07-16 2000-01-27 Viessmann Werke Kg Verfahren und Brenner zur Vermeidung von thermoakustischen Flamm- bzw. Druckschwingungen in mit gebläseunterstützten Brennern betriebenen Feuerungen
EP0985877A1 (fr) 1998-09-10 2000-03-15 Abb Research Ltd. Dispositif et procédé pour réduire au minimum les vibrations thermoacoustques dans les chambres de combustion de turbines à gaz
DE59810033D1 (de) 1998-09-16 2003-12-04 Alstom Switzerland Ltd Verfahren zum Minimieren thermoakustischer Schwingungen in Gasturbinenbrennkammern
EP1048898B1 (fr) 1998-11-18 2004-01-14 ALSTOM (Switzerland) Ltd Brûleur
DE59812039D1 (de) 1998-11-18 2004-11-04 Alstom Technology Ltd Baden Brenner
DE19928226A1 (de) 1999-05-07 2001-02-01 Abb Alstom Power Ch Ag Verfahren zur Unterdrückung bzw. Kontrolle von thermoakustischen Schwingungen in einem Verbrennungs-System sowie Verbrennungssystem zur Durchführung des Verfahrens

Also Published As

Publication number Publication date
US20020182553A1 (en) 2002-12-05
DE50110801D1 (de) 2006-10-05
EP1217295A3 (fr) 2002-11-20
EP1217295A2 (fr) 2002-06-26
US6773257B2 (en) 2004-08-10

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