WO2005093326A2 - Chambre a combustion de turbine a gaz et procede pour la faire fonctionner - Google Patents

Chambre a combustion de turbine a gaz et procede pour la faire fonctionner Download PDF

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Publication number
WO2005093326A2
WO2005093326A2 PCT/EP2005/051192 EP2005051192W WO2005093326A2 WO 2005093326 A2 WO2005093326 A2 WO 2005093326A2 EP 2005051192 W EP2005051192 W EP 2005051192W WO 2005093326 A2 WO2005093326 A2 WO 2005093326A2
Authority
WO
WIPO (PCT)
Prior art keywords
burner
combustion chamber
pressure pulsations
burners
arrangement
Prior art date
Application number
PCT/EP2005/051192
Other languages
German (de)
English (en)
Other versions
WO2005093326A3 (fr
Inventor
Peter Flohr
Alexander Ni
Rajeshriben Patel
Majed Toqan
Original Assignee
Alstom Technology Ltd
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 Ltd filed Critical Alstom Technology Ltd
Publication of WO2005093326A2 publication Critical patent/WO2005093326A2/fr
Publication of WO2005093326A3 publication Critical patent/WO2005093326A3/fr

Links

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
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2225/00—Measuring
    • F23N2225/08—Measuring temperature
    • F23N2225/16—Measuring temperature burner temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2237/00—Controlling
    • F23N2237/02—Controlling two or more 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 a combustion chamber for a gas turbine with the features of the preamble of claim 1.
  • the present invention also relates to a method for reducing pressure pulsations in such a combustion chamber with the features of the preamble of claim 7.
  • a lean premix combustion is generally carried out in order to burn a gaseous or liquid fuel with air with low pollutants.
  • the combustion air and fuel are premixed as evenly as possible and only then fed to the flame. This takes place with a high excess of air, so that relatively low flame temperatures arise, which reduces the formation of nitrogen oxides.
  • Combustion chambers of this type are susceptible to thermo-acoustic vibrations or pressure pulsations. On the one hand, such pressure pulsations lead to undesirable noise pollution in the vicinity of the combustion chamber. On the other hand, these pressure pulsations can
  • a combustion chamber of the type mentioned at the outset is known from EP 0597 138 B1, which has an annular combustion chamber and a plurality of burners which are arranged in a circumferential direction at an inlet of the combustion chamber.
  • several Helmholtz dampers are provided in the known combustion chamber, which communicate with the combustion chamber.
  • the pressure pulsations can be damped in the area of the combustion chamber.
  • a relatively large installation space is required, which, however, is not available in every application and, in particular, cannot be easily retrofitted.
  • the invention seeks to remedy this.
  • the invention as in the
  • the pressure pulsations occurring at the individual burners are preferably assessed on the basis of the amplitudes of the pressure pulsations occurring.
  • each individual burner is preferably one separate pressure sensor assigned, which enables the monitoring of the amplitudes.
  • a separate control circuit can be set up for each burner of the burner arrangement, which makes it possible to operate the respective burner in such a way that the amplitudes of any pulsations that occur locally remain below a predetermined or predeterminable threshold value. It is particularly important here that the control loops can work independently and therefore independently of the other control loops.
  • FIG. 1 is a very simplified schematic diagram of a combustion chamber according to the invention
  • Fig. 3 is a diagram in which the amplitudes of the pressure pulsations occurring for the burners of the combustion chamber is plotted.
  • the combustion chamber 1 shows, in a highly simplified form, a combustion chamber 1 for a gas turbine, which is otherwise not shown.
  • the combustion chamber 1 has an annular combustion chamber 2, of which an inlet 3 is visible in FIG. 1.
  • the combustion chamber 1 also comprises at least one ring-shaped burner arrangement 4, which consists of several burners 5. These burners 5 are arranged at the inlet 3 distributed in the circumferential direction. In the exemplary embodiment shown here, the burner arrangement 4 has twelve burners 5. It is clear that in another embodiment, more or fewer burners 5 can also be provided.
  • the burners 5 When the combustion chamber 1 is in operation, the burners 5 receive an oxidizer, in particular combustion air, and a liquid or gaseous fuel, e.g. Natural gas. A premixing of the fuel / combustion air mixture is then carried out in the burners 5. This fuel / combustion air mixture is then burned in the combustion chamber 2.
  • an oxidizer in particular combustion air
  • a liquid or gaseous fuel e.g. Natural gas
  • the combustion chamber 1 also includes an actuation system 6, which is designed such that it can actuate each burner 5 of the burner arrangement 4 individually. This is indicated in FIG. 1 by control lines 7, which each lead from the actuation system 6 to one of the burners 5. It is clear that another type of signal transmission can also be provided, for example by means of a bus system.
  • the actuation system 6 can set individually determined operating parameters for the respective burner 5 on each individual burner 5. For example, the actuation system 6 on each burner 5 adjust the air supply and / or fuel supply and / or burner inlet temperature.
  • the combustion chamber 1 is further equipped with a control system 8 and with a sensor system 9.
  • the sensor system 9 comprises several
  • These pressure sensors 10 are expediently designed such that an amplitude of pressure pulsations that occur in the area of the respectively assigned burner 5 can be detected.
  • the detected amplitudes or the measurement signals correlating therewith are made available to the control system 8 by the sensor system 9.
  • the control system 8 communicates with the sensor system 9.
  • the individual pressure sensors 10 are connected via signal lines 11 to a central unit 12 of the sensor system 9 and this communicates with the control system 8 via a connecting line 13.
  • each pressure sensor 10 can be connected directly to the control system 8.
  • a variant with a bus system is also conceivable, in which the individual pressure sensors 10 and the control system 8 are connected to a corresponding data bus.
  • the control system 8 is also connected to the actuation system 6 and configured in such a way that it can actuate the actuation system 6 for the targeted control of all or individual burners 5.
  • the variant according to FIG. 2 differs from the embodiment according to FIG. 1 primarily in that two annular burner arrangements 4 and 4 ′ are provided, which are arranged concentrically to one another.
  • Each burner arrangement 4, 4 ' here comprises the same number of burners 5 and 5', each burner 5 of the inner burner arrangement 4 having one burner 5 ' is assigned to the outer burner arrangement 4 ', the mutually assigned burners 5 and 5' also being spaced apart from one another in the radial direction.
  • the actuation system 6 is then designed in such a way that it controls the burners 5, 5 ′ assigned to one another in pairs.
  • each individual burner 5 and 5 ' is assigned its own pressure sensor 10 and in which the actuation system 6 can actuate each individual burner 5 and 5' individually.
  • FIG. 3 shows a situation that can typically occur during operation of the combustion chamber 1.
  • the diagram shows the amplitudes A determined with the aid of the pressure sensors 10, specifically for each individual burner 5.
  • the individual burners 5 are numbered from 1 to 12 in the diagram. In the arrangement according to FIG. 1, this numbering of the burners 5 corresponds, for example, to a numbering of
  • Burner 5 clockwise corresponding to a clock, that is, burner 5 2 is at the top, i.e. at the 12 o'clock position.
  • a threshold value As for the amplitude A of the pressure pulsations is also entered in the form of a broken line.
  • Pressure amplitudes A which are below the threshold value As represent "normal” pulsations in which there is no need for action.
  • the amplitudes A which are above the threshold value As are “critical”, so that there is a need for action in the associated burner 5.
  • the second burner 5 2) is thus the fifth Burner 5s, the eighth burner 5 ⁇ and the ninth burner 5g are critical, which is indicated in FIG. 1 by full circles, while the other burners 5 are not critical, that is to say operate normally and are indicated by circular lines or by empty circles.
  • the present invention works as follows:
  • the sensor system 9 monitors the amplitudes A of the pressure pulsations in the area of each individual burner 5 by means of the pressure sensors 10. The measured values are transmitted to the control system 8, which checks whether the determined amplitudes A are below the threshold value As or not.
  • control system 8 detects one for the four critical burners 5 2 , 5s, 5s and 5g
  • the control system 8 actuates the actuation system 6 in a suitable manner such that the actuation system 6 the critical burners 5 2 . 55, 5 ⁇ and 5g with regard to a reduction or suppression of the pressure pulsations or with a view to a weakening of the amplitudes A. It is essential here that the control system 8 uses the actuation system 6 exclusively the critical burners 5 2 . 5s, 5s and 5g controls to reduce the vibration amplitudes A, while all other, normally working burners 5 continue to be operated unchanged.
  • this procedure has the advantage that the measures for reducing the pressure pulsations, which are described below, have only a minor influence on the overall operating behavior of the burner chamber 1, since only the critical burners 5 and not all burners 5 are influenced.
  • the respective measures on the respective critical burner 5 can be selected very drastically and thus work effectively without critical operating states for the combustion chamber 1 occurring.
  • the pressure pulsations which build up are combated in this way at a very early point in time at which they have as a rule not yet adversely affected the operation of the combustion chamber 1, that is to say the combustion reaction in the combustion chamber 2.
  • the actuation system 6 can reduce the air supply and / or the fuel supply and / or the fuel inlet temperature, for example, on the respective burner 5. For example, throttling the fuel supply by, for example, 50% leads to an effective reduction in the pulsation amplitudes A. If the fuel supply is reduced by 50% for all four critical burners 5 2 , 5s, 5 8 and 5 g, this means one for the entire burner arrangement 4 Reduction of the fuel supply by only about 16.7%. Due to the drastic measures, the pulsation at the critical burners 5 can be combated very effectively, so that normal operation for the respective burner 5 can be achieved within a short time.
  • the burners 5 are controlled as a function of the amplitude A of the pressure pulsations occurring at the respective burner 5 in order to reduce the amplitudes A at the respective critical burner 5 from critical values above the threshold value As to non-critical or normal values below the threshold value As.
  • other reference variables for the control or regulation of the burners 5 are also conceivable, which correlate with the pressure pulsations on the individual burners 5. Since in the combustion chamber 1 according to the invention each burner 5 is assigned its own pressure sensor 10 and since the control system 8 also enables the individual burners 5 to be actuated individually via the actuation system 6, the burner arrangement 4 in the combustion chamber 1 according to the invention can have its own for each burner 5 closed loop are formed.
  • each individual control loop controls or controls the associated burner 5 independently of the other control loops with a view to reducing the pressure pulsations or with a view to reducing the amplitude A.
  • the control goal is not necessarily a specific value for the amplitude A, but rather that
  • control loops are therefore essentially only activated and operated only as long as the amplitude of the respective critical burner 5 is above the respective threshold value As.
  • the threshold value As can be a static absolute value, which is determined empirically, for example.
  • the threshold value As can also be a dynamic relative value, which results from an overall view of all current amplitudes A at the burners 5.
  • the relative threshold value As draws a limit for outliers that are no longer permissible with regard to an average of all amplitudes A or are regarded as critical.
  • a combination of a static absolute value and a dynamic relative value is also possible in order to also be able to take into account the rare case in which all the burners show 5 critical amplitudes.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Regulation And Control Of Combustion (AREA)

Abstract

La présente invention concerne une chambre à combustion (1) destinée à une turbine à gaz, laquelle comprend un espace de combustion (2) annulaire et au moins un ensemble annulaire de brûleurs (4) qui comporte plusieurs brûleurs (5) répartis, dans le sens périphérique, sur une entrée (3) de l'espace de combustion (2). Pour que les pulsations de pression dans l'espace de combustion (2) soient réduites, la chambre à combustion (1) comprend en outre un système d'actionnement (6) qui est conçu pour actionner individuellement chaque brûleur (5) de l'ensemble de brûleurs (4), ainsi qu'un système de commande (8) qui surveille, au moyen d'un système de détection (9) approprié, individuellement chaque brûleur (5) de l'ensemble de brûleur (4) et commande, par l'intermédiaire du système d'actionnement (6), chaque brûleur individuellement pour réduire les pulsations de pression.
PCT/EP2005/051192 2004-03-29 2005-03-16 Chambre a combustion de turbine a gaz et procede pour la faire fonctionner WO2005093326A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004015186.5 2004-03-29
DE102004015186A DE102004015186A1 (de) 2004-03-29 2004-03-29 Gasturbinen-Brennkammer und zugehöriges Betriebsverfahren

Publications (2)

Publication Number Publication Date
WO2005093326A2 true WO2005093326A2 (fr) 2005-10-06
WO2005093326A3 WO2005093326A3 (fr) 2006-02-09

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PCT/EP2005/051192 WO2005093326A2 (fr) 2004-03-29 2005-03-16 Chambre a combustion de turbine a gaz et procede pour la faire fonctionner

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DE (1) DE102004015186A1 (fr)
WO (1) WO2005093326A2 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1621811A1 (fr) * 2004-07-29 2006-02-01 ALSTOM Technology Ltd Procédé de fonctionnement pour un dispositif de combustion
EP1840464A1 (fr) * 2006-03-30 2007-10-03 ALSTOM Technology Ltd Chambre de combustion
US8631656B2 (en) 2008-03-31 2014-01-21 General Electric Company Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11703218B2 (en) 2017-02-03 2023-07-18 Siemens Energy Global GmbH & Co. KG Burner arrangement having a peripheral staging concept

Families Citing this family (1)

* Cited by examiner, † Cited by third party
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EP4148327A1 (fr) * 2021-09-09 2023-03-15 Ansaldo Energia Switzerland AG Moteur à turbine à gaz à stabilisation de mode acoustique, procédé de commande et procédé de modification de moteur à turbine à gaz

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DE4414232A1 (de) * 1994-04-23 1995-10-26 Abb Management Ag Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
US5533329A (en) * 1993-05-17 1996-07-09 Hitachi, Ltd. Control apparatus for and control method of gas turbine
US5544478A (en) * 1994-11-15 1996-08-13 General Electric Company Optical sensing of combustion dynamics
EP0962704A2 (fr) * 1998-05-29 1999-12-08 United Technologies Corporation Procédé et dispositif pour fonctionner un brûleur à gaz
US6205764B1 (en) * 1997-02-06 2001-03-27 Jakob Hermann Method for the active damping of combustion oscillation and combustion apparatus
EP1096201A1 (fr) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brûleur
EP1180646A1 (fr) * 2000-08-10 2002-02-20 ROLLS-ROYCE plc Chambre de combustion
US6464489B1 (en) * 1997-11-24 2002-10-15 Alstom Method and apparatus for controlling thermoacoustic vibrations in a combustion system
EP1255074A1 (fr) * 2001-05-01 2002-11-06 ABB Schweiz AG Diminution des oscillations dans une chambre de combustion

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US5487266A (en) * 1992-05-05 1996-01-30 General Electric Company Combustion control for producing low NOx emissions through use of flame spectroscopy
DE19636093B4 (de) * 1996-09-05 2004-07-29 Siemens Ag Verfahren und Vorrichtung zur akustischen Modulation einer von einem Hybridbrenner erzeugten Flamme

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5533329A (en) * 1993-05-17 1996-07-09 Hitachi, Ltd. Control apparatus for and control method of gas turbine
DE4414232A1 (de) * 1994-04-23 1995-10-26 Abb Management Ag Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
US5544478A (en) * 1994-11-15 1996-08-13 General Electric Company Optical sensing of combustion dynamics
US6205764B1 (en) * 1997-02-06 2001-03-27 Jakob Hermann Method for the active damping of combustion oscillation and combustion apparatus
US6464489B1 (en) * 1997-11-24 2002-10-15 Alstom Method and apparatus for controlling thermoacoustic vibrations in a combustion system
EP0962704A2 (fr) * 1998-05-29 1999-12-08 United Technologies Corporation Procédé et dispositif pour fonctionner un brûleur à gaz
EP1096201A1 (fr) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brûleur
EP1180646A1 (fr) * 2000-08-10 2002-02-20 ROLLS-ROYCE plc Chambre de combustion
EP1255074A1 (fr) * 2001-05-01 2002-11-06 ABB Schweiz AG Diminution des oscillations dans une chambre de combustion

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1621811A1 (fr) * 2004-07-29 2006-02-01 ALSTOM Technology Ltd Procédé de fonctionnement pour un dispositif de combustion
US7513117B2 (en) 2004-07-29 2009-04-07 Alstom Technology Ltd Method for operating a furnace
EP1840464A1 (fr) * 2006-03-30 2007-10-03 ALSTOM Technology Ltd Chambre de combustion
US7901203B2 (en) 2006-03-30 2011-03-08 Alstom Technology Ltd. Combustion chamber
US8631656B2 (en) 2008-03-31 2014-01-21 General Electric Company Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
US11703218B2 (en) 2017-02-03 2023-07-18 Siemens Energy Global GmbH & Co. KG Burner arrangement having a peripheral staging concept
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Also Published As

Publication number Publication date
WO2005093326A3 (fr) 2006-02-09
DE102004015186A1 (de) 2005-10-20

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