EP2383514A1 - Système de brûleur et procédé d'amortissement d'un tel système de brûleur - Google Patents

Système de brûleur et procédé d'amortissement d'un tel système de brûleur Download PDF

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Publication number
EP2383514A1
EP2383514A1 EP10161299A EP10161299A EP2383514A1 EP 2383514 A1 EP2383514 A1 EP 2383514A1 EP 10161299 A EP10161299 A EP 10161299A EP 10161299 A EP10161299 A EP 10161299A EP 2383514 A1 EP2383514 A1 EP 2383514A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
hat
burner
resonator
head end
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.)
Withdrawn
Application number
EP10161299A
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German (de)
English (en)
Inventor
Sven Bethke
Michael Huth
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP10161299A priority Critical patent/EP2383514A1/fr
Priority to PCT/EP2011/053880 priority patent/WO2011134713A1/fr
Publication of EP2383514A1 publication Critical patent/EP2383514A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • 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 system with at least one burner, with a combustion chamber and a head end, the latter comprising at least one fuel injection and a fuel-air premix, wherein the burner has a hat with a hat side and a hat top, wherein at least the Hutoberseite seen in the flow direction is arranged in front of the head end, wherein between the hat top and the head end thereby a burner plenum is formed, wherein the hat has a combustion chamber facing side and a combustion chamber side facing away. Furthermore, the invention relates to a method for damping vibrations of such a burner system.
  • a gas turbine plant comprises in the simplest case a compressor, a combustion chamber and a turbine.
  • the compressor there is a compression of sucked air, which is then admixed with a fuel.
  • the combustion chamber the mixture is combusted, the combustion exhaust gases being supplied to the turbine, from which energy is withdrawn from the combustion exhaust gases and converted into mechanical energy.
  • thermoacoustic oscillations in the combustion chambers of gas turbines - or turbomachines in general - represent a problem in the design and operation of new combustors, combustor parts and burners for such turbomachines.
  • thermoacoustic vibrations can increase. This can lead to an oscillating interaction between thermal and acoustic disturbances, which can cause high loads on the combustion chamber and rising emissions.
  • thermoacoustically induced instabilities are significantly influenced by the acoustic properties of the combustion chamber and the boundary conditions present at the combustion chamber inlet and the combustion chamber outlet as well as at the combustion chamber walls.
  • Helmholtz resonators are used for damping, which dampen the amplitude of vibrations of certain frequencies.
  • a Helmholtz resonator typically includes a volume of air or other gas therein. The volume is followed by a neck, the so-called resonator neck, which also contains air or gas and which opens into the combustion chamber.
  • the air or the gas in the volume and the resonator neck form a spring-mass system, wherein the air or the gas in the volume of the spring and the air or the gas in the resonator neck forms the mass.
  • the spring-mass system oscillates at a resonant frequency determined by the volume, the cross-sectional area of the resonator neck, and the length of the resonator neck, the Helmholtz resonator behaves like an infinite-length opening which prevents a standing wave from interfering with itself can form the resonance frequency.
  • the WO 93/10401 A1 shows a device for suppressing combustion oscillations in a combustion chamber of a gas turbine plant.
  • a Helmholtz resonator is fluidically connected to a fuel supply line. The acoustic properties of the supply line or the overall acoustic system are thereby changed so that combustion oscillations are suppressed. It has, however shown that this measure is not sufficient in all operating conditions, as it can lead to combustion oscillations even with a suppression of vibrations in the fuel line.
  • the WO 03 / 074936A1 shows a gas turbine, with a burner which opens into a combustion chamber, said mouth is annularly surrounded by a Helmholtz resonator.
  • a Helmholtz resonator As a result, combustion vibrations are effectively attenuated by close contact with the flame, while avoiding temperature nonuniformity.
  • Helmholz resonator tubes are mounted, which cause a frequency adjustment.
  • a gas turbine combustor which has air-purged Helmholtz resonators in the burner.
  • the resonators are arranged alternately on the end face of the combustion chamber between the burners. By these resonators, vibration energy is absorbed by combustion vibrations occurring in the combustion chamber and the combustion vibrations are thereby damped.
  • the object of the present invention is therefore to specify a burner system which can be used for damping combustion oscillations and which avoids the above problem. Another object is to specify a method which can be used to dampen combustion oscillations and which avoids the above problem.
  • a burner system is provided with at least one burner, with a combustion chamber and a head end, the latter comprising at least one fuel injection and a fuel-air premix.
  • the burner has a hat with a hat side and a hat top, wherein at least the hat top side is arranged in the flow direction in front of the head end. Between the Hutoberseite and the head end becomes a burner plenum educated.
  • the hat has a side facing the combustion chamber and a side facing away from the combustion chamber.
  • c is the speed of sound in the medium
  • V is the volume of the resonator chamber
  • L is the length
  • S is the area of the resonator neck between the resonator chamber and the surroundings.
  • the volume V thus influences the resonant frequency of the resonator.
  • the volume in the resonator chamber behaves like a spring and the fluid mass in the neck behaves like the mass of a mechanical spring-mass system.
  • the resonator acts as an absorber by displacing the pressure oscillation impressed on it at the beginning of the resonator neck to a frequency different from that produced in the combustion chamber.
  • influences such as fluid friction, etc., significantly alter the effectiveness of the resonators, so that they do not act as sound absorbers, but as sound absorbers, although the sound amplitude is reduced only, and can not be erased by far.
  • the essential excitation mechanism can not be interrupted by this arrangement become. Pressure and sound velocity in the burner itself are not affected.
  • the hat now has at least one resonator on its side facing away from the combustion chamber. This is particularly advantageous over the prior art, in which the resonators are mounted directly on the combustion chamber or on the combustion chamber outer wall, since the pressure fluctuations are already prevented or suppressed in the burner plenum.
  • the hat side is at least partially arranged around the head end, so that in this case the hat side is spaced in a radial direction from the head end.
  • a channel is formed by the hat side and the head end. Through this channel compressor air is directed to the plenum. This compressor air thus cools the outside of the combustion chamber and thus reduces overheating of the combustion chamber. Ideally, the compressor air is preheated so that a more stable combustion can take place.
  • the resonator is a Helmholtz resonator.
  • the Helmholtz resonator on a neck which is adjustable in length. This can be, for example be realized via an adjustable sleeve. Thus, different frequencies can be damped in the combustion chamber.
  • the resonator is provided on the side facing away from the combustion chamber.
  • the resonator neck has openings to the plenum.
  • the installation of the Helmholtz resonator in the area of the plenum gives the advantage over lower temperatures compared to the attachment to the combustion chamber.
  • a flow through the resonators with cooling air is namely not necessary. This eliminates the cooling holes on the back of the resonators, which reduce the effectiveness of the resonators.
  • each burner having a hat with at least one resonator on its combustion chamber side facing away.
  • the vibrations in the entire gas turbine can be reduced.
  • a gas turbine comprises such a burner system.
  • the method related object is achieved by the disclosure of a method for damping vibrations of a burner system with at least one burner, with a combustion chamber and a head end, the latter comprises at least one fuel injection and a fuel-air premix, the burner having a hat with a Hutseite and a Hutoberseite, wherein at least the hat top side seen in the flow direction is arranged in front of the head end, wherein between the Hutoberseite and the head end thereby a burner plenum is formed, wherein the hat has a combustion chamber facing side and a combustion chamber side facing away by at least one Resonator on the hat on its side facing away from the combustion chamber vibrations in the burner plenum are avoided, thereby avoiding or at least reducing inherent modes of the combustion chamber.
  • thermoacoustic vibrations are largely prevented or even avoided and also prevents speed fluctuations in the fuel injection / fuel-air premixing.
  • FIG. 1 shows by way of example a gas turbine 1 in a longitudinal partial section.
  • the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3 with a shaft, which is also referred to as a turbine runner.
  • a suction housing 4 Along the rotor 3 follow one another a suction housing 4, a compressor 5, for example, a toroidal combustion chamber 6, with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing. 9
  • the combustion chamber 6 communicates with, for example, a hot gas channel 11.
  • a hot gas channel 11 There, for example, four turbine stages 12 connected in series form the turbine 8.
  • Each turbine stage 12 is formed for example of two blade rings. As seen in the direction of flow of a working medium 13, a row 25 of blades 25 follows in the hot gas channel 11 of a row of guide vanes 15.
  • the burner 7 in conjunction with a so-called tube combustion chamber 6 ( Fig. 2 ) used.
  • the gas turbine 1 has a plurality of annularly arranged tube combustion chambers 6, whose outflow openings open into the annular hot gas channel 11 turbine inlet side.
  • a plurality, for example six or eight, burner 7 is arranged at the opposite end of the downstream opening of the tube combustion chamber 6 usually annularly around a pilot burner.
  • FIG. 2 shows a section of a tube burner 7 schematically.
  • the burner 7 comprises a head end 51, a transition 52 and a liner 53 therebetween.
  • the "head end 51” is essentially the subsection of the fuel injection 55 / fuel-air premix 56 of the burner.
  • the liner 53 extends from the head end to the transition 52 in any manner.
  • an annular passage 57 is formed by the combustion / cooling air 65 flows.
  • the space before the fuel injection 55 or fuel / air premix 56 is referred to as burner plenum (plenum) 100.
  • the burner 7 has a hat 110 with a hat side 150 and a hat top 170.
  • the hat top 170 is seen in the flow direction arranged in front of the head end 51, whereby between the Hutoberseite 170 and the head end 51, a burner plenum 100 is formed.
  • the hat 110 has a combustion chamber-facing side 140 and a combustion chamber-facing side 120 (FIG. Fig. 3 ). In this case, the hat 110 with the hat side 150 is arranged virtually outside the machine.
  • FIG. 3 shows the burner system according to the invention with at least one burner 7 with a combustion chamber 6 and a head end 51.
  • the hat 110 therefore has, according to the invention, at least one resonator 200, on its side 120 remote from the combustion chamber, for the most part, several Helmholtz resonators 200. These suppress the pressure oscillations in the plenum 100 in front of the combustion chamber 6. This is particularly advantageous when it comes to tube combustion chambers 6.
  • the resonator 200 in this case has a neck 201, which is adjustable in length. This can be realized via an adjustable sleeve. Thus, different frequencies can be damped.
  • the Helmholtz resonators 200 are provided on the side facing away from the combustion chamber 120. There is a realization particularly easy to implement. In addition, so speed fluctuations in the fuel injection 55 and the fuel-air premix 56 are prevented.
  • the resonator neck 201 has openings to the plenum 100.
  • the realization of the Helmholtz resonators 200 in the region of the plenum 100 gives the advantage over the attachment to the combustion chamber of lower temperatures than when mounted on the combustion chamber outside. A flow through the Helmholtz resonators 200 with Cooling air is therefore not necessary. This eliminates necessary cooling air holes on the Helmholtz resonators 200, which reduce the effectiveness of the Helmholtz resonators 200.
EP10161299A 2010-04-28 2010-04-28 Système de brûleur et procédé d'amortissement d'un tel système de brûleur Withdrawn EP2383514A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP10161299A EP2383514A1 (fr) 2010-04-28 2010-04-28 Système de brûleur et procédé d'amortissement d'un tel système de brûleur
PCT/EP2011/053880 WO2011134713A1 (fr) 2010-04-28 2011-03-15 Système de combustion pour amortir un système de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10161299A EP2383514A1 (fr) 2010-04-28 2010-04-28 Système de brûleur et procédé d'amortissement d'un tel système de brûleur

Publications (1)

Publication Number Publication Date
EP2383514A1 true EP2383514A1 (fr) 2011-11-02

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EP10161299A Withdrawn EP2383514A1 (fr) 2010-04-28 2010-04-28 Système de brûleur et procédé d'amortissement d'un tel système de brûleur

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EP (1) EP2383514A1 (fr)
WO (1) WO2011134713A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2715232A1 (fr) * 2011-05-25 2014-04-09 General Electric Company Dispositif de combustion à collecteur bidirectionnel pour amortissement dynamique

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993010401A1 (fr) 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
EP0597138A1 (fr) 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs
US20020100281A1 (en) * 2000-11-25 2002-08-01 Jaan Hellat Damper arrangement for reducing combustion-chamber pulsations
WO2003074936A1 (fr) 2002-03-07 2003-09-12 Siemens Aktiengesellschaft Turbine a gaz
EP1568869A1 (fr) * 2002-12-02 2005-08-31 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
GB2443838A (en) * 2006-11-16 2008-05-21 Rolls Royce Plc Combustion Control for a Gas Turbine
US20100011769A1 (en) * 2008-07-16 2010-01-21 Siemens Power Generation, Inc. Forward-section resonator for high frequency dynamic damping

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993010401A1 (fr) 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
EP0597138A1 (fr) 1992-11-09 1994-05-18 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs
US20020100281A1 (en) * 2000-11-25 2002-08-01 Jaan Hellat Damper arrangement for reducing combustion-chamber pulsations
WO2003074936A1 (fr) 2002-03-07 2003-09-12 Siemens Aktiengesellschaft Turbine a gaz
EP1568869A1 (fr) * 2002-12-02 2005-08-31 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
GB2443838A (en) * 2006-11-16 2008-05-21 Rolls Royce Plc Combustion Control for a Gas Turbine
US20100011769A1 (en) * 2008-07-16 2010-01-21 Siemens Power Generation, Inc. Forward-section resonator for high frequency dynamic damping

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Publication number Publication date
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