EP0961906B1 - Procede d'attenuation active d'une oscillation de combustion, et utilisation de la procede - Google Patents

Procede d'attenuation active d'une oscillation de combustion, et utilisation de la procede Download PDF

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Publication number
EP0961906B1
EP0961906B1 EP98906838A EP98906838A EP0961906B1 EP 0961906 B1 EP0961906 B1 EP 0961906B1 EP 98906838 A EP98906838 A EP 98906838A EP 98906838 A EP98906838 A EP 98906838A EP 0961906 B1 EP0961906 B1 EP 0961906B1
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EP
European Patent Office
Prior art keywords
combustion
fuel
supplied
combustion chamber
oscillation
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
EP98906838A
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German (de)
English (en)
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EP0961906A1 (fr
Inventor
Jakob Hermann
Carl-Christian Hantschk
Peter Zangl
Dieter Vortmeyer
Armin Orthmann
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Siemens AG
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Siemens AG
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Publication date
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/16—Systems for controlling combustion using noise-sensitive detectors
    • 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
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means
    • 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 method for active damping Combustion vibration in a combustion chamber and one corresponding combustion device.
  • Active damping of a combustion oscillation is achieved in that an actuator (Piezo actuator) the amount of fuel supplied to a burner modulated.
  • a microphone picks up the acoustic vibrations the combustion chamber.
  • the microphone signal becomes a control signal for regulating the modulation of the amount of fuel supplied so derived that the modulation of the supplied
  • the amount of fuel is counter-cyclical to the combustion oscillation.
  • WO93 / 10401 A discloses a burner arrangement with two Burners in a common combustion chamber.
  • the burner fuel can be supplied via a fuel line.
  • an acoustically effective element coupled to the Fuel line.
  • This is preferably a passive element, e.g. in the form of a Helmholtz resonator, through which the acoustic Properties of the fuel line are changed, i.e. by which the fuel line is acoustically detuned.
  • the acoustically effective Element is a loudspeaker that is transmitted to the Fuel flow acts in the fuel line.
  • the loudspeaker is controlled according to the only disclosed embodiment via an outside of the Combustion chamber arranged microphone.
  • the object of the invention is to provide a simple method for active Damping a combustion vibration in a combustion chamber specify.
  • WO 98/10226 shows a method for damping a Combustion vibration in the combustion chamber of a gas turbine.
  • the active combustion oscillation is modulated by a Pilot fuel flow reached.
  • the main fuel flow remains unmodulated.
  • the modulation of the Pilot fuel flow necessary actuators can due the comparatively small amount of fuel so executed that they meet the quick regulatory requirements suffice.
  • volume 096 no .: 002, 29. February 1996 becomes the fuel fed to a burner divided in different ways. This happens via an injection of the fuel over two Nozzles. The two nozzles are controlled via a Sensor signal.
  • the object directed at the method is solved by Specification of a method for actively damping a combustion oscillation in a combustion chamber with a control the actuators take place via a number of measured variables which is smaller than the number of actuators, the Measurements of the characterization of the combustion vibration serve and wherein the control of at least one Actuator about a symmetry of the combustion vibration is determined.
  • a manipulated variable means a system variable which is described by a physical quantity z. B. a quantity supplied at a certain point Fuel. Another manipulated variable would be z. B. an amount of fuel supplied elsewhere, or z. B. a lot of supplied combustion air.
  • An actuator is accordingly not mandatory as an apparatus Unity.
  • the designation actuator can also comprise two or more means, together a steep size influence, e.g. B. two speakers in common modulate a mass flow of combustion air.
  • Combustion is supplied with fuel and combustion air, preferably a quantity of the combustion as the manipulated variable supplied fuel and / or a lot of the Combustion supplied combustion air can be used but other control variables are also used at the same time can be.
  • the fuel mass flow is preferred and / or the combustion air mass flow modulated. So that is it is possible to actively dampen a combustion vibration about the modulation of the amount of fuel supplied and / or the amount of combustion air supplied.
  • a combustion vibration forms in the combustion chamber an acoustic natural vibration or a sound field.
  • a sound field is characterized by characteristic sound field sizes, such as. Sound pressure and sound speed marked, their time courses have certain periodic regularities.
  • a sound field typically has spatial areas within which the sound field sizes with different Periodically oscillate amplitudes. Sound field sizes in different spatial areas of the sound field are temporal in their vibrations to each other, in one for characteristic of the sound field shifted, they point thus a characteristic phase shift. Point the spatial areas described have a certain regularity in their characteristics, one speaks of symmetry of the sound field.
  • the acoustic Characterized natural vibration From this knowledge of the existing sound field is about the symmetry of the acoustic natural vibration in the combustion chamber the control the actuators derived by the respective spatial Position is taken into account at which an actuator Combustion vibration affects. Are preferred just like that many measurands determined how it is for characterization the natural vibration is required. With the characterization the acoustic natural vibration is known which Phase and amplitude of the combustion vibration at the location of one Has engagement of an actuator. This results in the Regulation necessary for damping the combustion vibration each actuator. The number of measuring points is therefore only through those necessary to characterize the natural vibration Number of measuring points defined.
  • the actuators are also preferred to be countercyclical Combustion vibration controlled.
  • An anti-cyclical control causes a particularly efficient damping of the combustion vibration.
  • An anti-cyclical control is called one inverted to self-excited combustion vibration Fluctuation of the manipulated variable. For a harmonic combustion vibration this means that the manipulated variable with same frequency, but is impressed in phase opposition.
  • the process is preferably carried out in an annular combustion chamber applied to a gas turbine.
  • An annular combustion chamber one Gas turbine has a relatively large number of burners, which can each excite a combustion oscillation. It is desirable for each burner with its own actuator active damping of a combustion oscillation to be able to perform. The number of measured variables to be determined for these actuators can be kept small.
  • Two or more actuators can be present in that a modulation device comprises two or more actuators or in that two or more modulation devices are present.
  • This combustion device it is possible to reduce the necessary number of regulators and sensors and thus to reduce the design effort and actively dampen a combustion oscillation perform. The savings in sensors and controllers achieved in this way lead to considerable cost savings.
  • a burner preferably has a fuel supply in each case and a combustion air supply, at least an actuator with the fuel supply or with Combustion air supply is connected. It is possible the damping of a combustion vibration by a Regulation of the amount of fuel supplied or the amount supplied Amount of combustion air. At the same time, too one actuator or several actuators another Modulate the manipulated variable or other manipulated variables.
  • the burners are preferably hybrid burners, each comprising a premix burner and a pilot burner.
  • the principle of a hybrid burner is described in the article "Progress in NO x and CO Emission Reduction of Gas Turbines", H. Maghon, P. Behrenbrink, H. Termuehlen and G. Gartner, ASME / IEEE Power Generation Conference, Boston, October 1990 , which is hereby explicitly referred to.
  • the combustion chamber is preferably an annular combustion chamber Gas turbine.
  • the only figure shows schematically one along an axis 31 directed gas turbine 33.
  • a compressor 2 is fluidic connected to a turbine 3. Between compressor 2 and turbine 3, a combustion device 1 is connected.
  • the combustion device 1 consists of a combustion chamber 4, open into the hybrid burner 5.
  • Any hybrid burner 5 is made up of a conical premix burner 6, which simultaneously forms a combustion air supply 6a.
  • the premix burner 6 surrounds a pilot burner 7 with its own Combustion air supply 7a.
  • Each premix burner is 6
  • Each Pilot burner 7 becomes fuel 28 via a fuel feed line 24 fed.
  • the hybrid burners 5 are part in the combustion chamber 4, the other part in one of the combustion chamber 4 adjacent pre-chamber 4a arranged.
  • each Fuel supply line 24 of the pilot burner 7 is an actuator 8 installed.
  • the actuators 8 are electrically connected to a common control logic 9. This is electrically connected with a controller 10.
  • the controller 10 is in turn electrical connected to a pressure sensor 11, in particular a Piezo pressure sensor 11.
  • the pressure sensor 11 is at a measuring point 11a arranged in the combustion chamber 4.
  • combustion air 29 is in the Compressor 2 is compressed and via a channel 21 into the prechamber 4a headed.
  • the combustion air comes from the pre-chamber 4a 29 into the air supply channels 6a, 7a of the premix burner 6 and the pilot burner 7.
  • the pilot burners 7 are supplied with fuel 28 and in the combustion air 29 burned as a pilot flame.
  • the premix burners 6 becomes fuel 28 via the fuel feed lines 23 supplied and mixed with the combustion air 29.
  • the fuel-air mixture entering the combustion chamber 4 ignites on the pilot flame.
  • combustion vibration Through an interaction with the acoustics of the combustion chamber 4 a Train combustion vibration.
  • Such a combustion vibration causes an acoustic natural vibration 30 or a sound field 30 in the combustion chamber 4.
  • this acoustic natural vibration 30 is measured.
  • the Pressure sensor 11. outputs a measurement signal.
  • This measurement signal is converted into a control signal in the controller 10. From this control signal is a control with the help of control logic 9 determined for the actuators 8. This results in the control from the spatial position of a burner 5 and from the symmetry of the acoustic natural vibration 30.
  • the Fuel supply for the pilot burner 7 becomes countercyclical regulated for combustion vibration, that is, the fuel mass flow each pilot burner 7 is modulated so that the amount of fuel injected into the combustion chamber 4 Location of the flame or the combustion zone of the respective pilot burner 7 in phase opposition and with the same frequency as that Combustion vibration changes in time at the location of the flame. In order to damping of the combustion vibration results.
  • the Activation of the actuators 8 therefore requires a measurement only one measuring point 11a.
  • a sensor 11 and a controller 10 are saved.
  • the method is also especially for a combustion chamber 4 more than two burners 5 are suitable, for example for an annular combustion chamber, or for a silo combustion chamber with e.g. eight burners.
  • the number of sensors 11 and controllers 10 is preferably such great as it is for the characterization of the acoustic natural vibration 30 is just required.

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

Abstract

La présente invention concerne un procédé d'atténuation active d'une oscillation de combustion dans une chambre de combustion (4) dotée d'au moins deux organes de réglage (8). Le procédé se caractérise en ce qu'une commande des organes de réglage (8) exige que l'oscillation de combustion soit mesurée en un nombre de points plus faible qu'il n'y a d'organes (8). On y arrive essentiellement en exploitant la symétrie d'une oscillation acoustique générée par autoexcitation (30) à l'intérieur de la chambre de combustion (4).

Claims (5)

  1. Procédé pour l'atténuation active d'une oscillation de combustion dans une chambre de combustion (4) comportant au moins deux brûleurs (5) auxquels est amené respectivement au moins un fluide (28, 29) pour la combustion, dans lequel l'oscillation de combustion est atténuée par la commande d'au moins deux organes de réglage (8) qui influencent chacun une grandeur réglante, dans lequel chaque grandeur réglante est une quantité d'un fluide (28, 29) amené respectivement à un brûleur et dans lequel une grandeur mesurée est déterminée à au moins un endroit de mesure (11 a),
       caractérisé par le fait qu'on effectue une commande des organes de réglage (8) par l'intermédiaire d'un nombre de grandeurs mesurées qui est plus petit que le nombre d'organes de réglage (8), les grandeurs mesurées servant à la caractérisation de l'oscillation de combustion et la commande d'au moins un organe de réglage (8) étant déterminée par l'intermédiaire d'une symétrie de l'oscillation de combustion.
  2. Procédé selon la revendication 1,
       caractérisé par le fait qu'on utilise comme grandeur réglante une quantité de combustible (28) amené à la combustion ou une quantité d'air de combustion (29) amené à la combustion.
  3. Procédé selon la revendication 1 ou 2,
       caractérisé par le fait qu'on détermine exactement autant de grandeurs mesurées que nécessaire pour une caractérisation de l'oscillation de combustion.
  4. Procédé selon l'une des revendications précédentes,
       caractérisé par le fait qu'on commande les organes de réglage (8) de façon anticyclique par rapport à l'oscillation de combustion.
  5. Utilisation du procédé selon l'une des revendications précédentes dans une chambre de combustion annulaire (4) d'une turbine à gaz (1).
EP98906838A 1997-02-06 1998-01-23 Procede d'attenuation active d'une oscillation de combustion, et utilisation de la procede Expired - Lifetime EP0961906B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19704540 1997-02-06
DE19704540A DE19704540C1 (de) 1997-02-06 1997-02-06 Verfahren zur aktiven Dämpfung einer Verbrennungsschwingung und Verbrennungsvorrichtung
PCT/DE1998/000211 WO1998035186A1 (fr) 1997-02-06 1998-01-23 Procede d'attenuation active d'une oscillation de combustion, et dispositif de combustion

Publications (2)

Publication Number Publication Date
EP0961906A1 EP0961906A1 (fr) 1999-12-08
EP0961906B1 true EP0961906B1 (fr) 2003-06-04

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US (1) US6205764B1 (fr)
EP (1) EP0961906B1 (fr)
JP (1) JP4130479B2 (fr)
DE (2) DE19704540C1 (fr)
WO (1) WO1998035186A1 (fr)

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GB2375601A (en) 2001-05-18 2002-11-20 Siemens Ag Burner apparatus for reducing combustion vibrations
JP4056232B2 (ja) † 2001-08-23 2008-03-05 三菱重工業株式会社 ガスタービン制御装置、ガスタービンシステム及びガスタービン遠隔監視システム
DE10213682A1 (de) * 2002-03-27 2003-10-09 Alstom Switzerland Ltd Verfahren und Vorrichtung zur Kontrolle von thermoakustischen Instabilitäten bzw. Schwingungen in einem Verbrennungssystem
DE60228085D1 (de) 2002-09-20 2008-09-18 Siemens Ag Vormischbrenner mit profilierter Luftmassenströmung
DE10257275A1 (de) * 2002-12-07 2004-06-24 Alstom Technology Ltd Verfahren und Vorrichtung zur Beeinflussung thermoakustischer Schwingungen in Verbrennungssystemen
DE102004015187A1 (de) * 2004-03-29 2005-10-20 Alstom Technology Ltd Baden Brennkammer für eine Gasturbine und zugehöriges Betriebsverfahren
DE102004015186A1 (de) * 2004-03-29 2005-10-20 Alstom Technology Ltd Baden Gasturbinen-Brennkammer und zugehöriges Betriebsverfahren
US7775052B2 (en) * 2004-05-07 2010-08-17 Delavan Inc Active combustion control system for gas turbine engines
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US8162287B2 (en) * 2005-12-29 2012-04-24 Delavan Inc Valve assembly for modulating fuel flow to a gas turbine engine
US7665305B2 (en) 2005-12-29 2010-02-23 Delavan Inc Valve assembly for modulating fuel flow to a gas turbine engine
US7584617B2 (en) 2006-03-17 2009-09-08 Siemens Energy, Inc. Monitoring health of a combustion dynamics sensing system
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Also Published As

Publication number Publication date
DE19704540C1 (de) 1998-07-23
WO1998035186A1 (fr) 1998-08-13
DE59808633D1 (de) 2003-07-10
JP4130479B2 (ja) 2008-08-06
JP2001510550A (ja) 2001-07-31
EP0961906A1 (fr) 1999-12-08
US6205764B1 (en) 2001-03-27

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EP1429004B1 (fr) Méthode et dispositif influençant les oscillations thermoacoustiques dans les systèmes de combustion

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