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EP2962039A1 - Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques - Google Patents

Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques

Info

Publication number
EP2962039A1
EP2962039A1 EP14707733.3A EP14707733A EP2962039A1 EP 2962039 A1 EP2962039 A1 EP 2962039A1 EP 14707733 A EP14707733 A EP 14707733A EP 2962039 A1 EP2962039 A1 EP 2962039A1
Authority
EP
European Patent Office
Prior art keywords
channel
resonator
damping device
housing
gas turbine
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Withdrawn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
EP14707733.3A
Other languages
German (de)
English (en)
Inventor
Christian Beck
Jaap Van Kampen
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP14707733.3A priority Critical patent/EP2962039A1/fr
Publication of EP2962039A1 publication Critical patent/EP2962039A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
    • 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

  • Damping device for a gas turbine, gas turbine and method for damping thermoacoustic vibrations
  • the invention relates to a damping device for a gas turbine with at least one Helmholtz resonator and at least one channel with a channel casing.
  • the Helmholtz resonator comprises a resonator housing and at least one resonator neck tube, wherein the resonator housing encloses a resonance volume of the Helmholtz resonator into which acoustic oscillations can be coupled by means of the resonator neck tube.
  • the channel has at least one outlet opening.
  • the invention also relates to a gas turbine with at least one combustion chamber and at least one such damping device and to a method for damping thermoacoustic oscillations.
  • a gas turbine in the simplest case comprises a compressor, a combustion chamber and a turbine.
  • the compressor In the compressor there is a compression of sucked air, which is then admixed with a fuel.
  • a combustion of the mixture In the combustion chamber, a combustion of the mixture, whereby a hot Hägastrom arises, which is supplied to the turbine. This removes energy from the hot working gas and converts it into mechanical energy.
  • the combustion chamber there may be an interaction of acoustic oscillations and fluctuations in the heat release, which can swell each other.
  • Such thermoacoustic oscillations which occur in particular in the combustion chamber of the gas turbine, can lead to considerable damage to the components during operation of the gas turbine and force shutdown of the system.
  • Helmholtz resonators for vibration damping are used in the prior art, for example, which effectively dampen the amplitude of vibrations within a certain frequency band.
  • purge air is introduced into the resonator neck in the opposite direction of the hot gas intake direction.
  • EP 0 597 138 A1 discloses a gas turbine combustor. Helmholtz resonators purged with purging air are arranged in the area of the burners.
  • the Helmholtz resonators each comprise a resonator housing, which encloses the resonance volume and a damping tube, which also with
  • Resonator neck tube or resonator neck can be called.
  • the damping tube connects the resonance volume with the environment, so that acoustic vibrations can be coupled into the resonance volume.
  • a scavenging air introducing feed pipe opens into the resonator housing, so that the scavenging air is introduced into the resonance volume and flushes the damping tube opposite to the H disclosegaseinzug.
  • a disadvantage of this technique is that the performance of the Helmholtz resonator decreases with increasing speed of the purging air in the damping tube. Also, the compressor air used for purging is not available as combustion air, which adversely affects the achieved emissions of the gas turbine.
  • the invention has for its object to provide a damping device of the type mentioned and a gas turbine with such a damping device, which allows a particularly effective damping of thermoacoustic oscillations.
  • the object is achieved in a damping device of the type mentioned in that Acoustic vibrations of a fluid flow flowing through a burner plenum and a combustion chamber can be coupled into the outlet opening of the channel and the coolant can be acted upon by the channel, the at least one
  • Resonator neck tube on the hot gas side upstream of the at least one outlet opening in such a channel.
  • the resonator neck tube of the Helmholtz resonator is no longer flushed, but the hot gas side outlet of the resonator neck tube opens into a channel acted upon by cooling fluid.
  • the temperature of the transmission medium of the acoustic waves in the mouth region of the resonator neck tube is lowered relative to the temperatures prevailing in the combustion chamber or the burner plenum of the gas turbine.
  • the mouth of the resonator neck tube and the hot, thermoacoustic vibration producing source always separate a portion of the channel which is cooled by cooling fluid. Only the at least one outlet opening of the channel can be exposed to a hot gas intake.
  • the channel may be supplied with cooling fluid in such a way that it is flushed with purging air in the opposite direction to the hot gas intake direction.
  • the channel can also be cooled in a different way. Essential here is only that the channel is acted upon by cooling fluid, that cools the located inside the channel transmission medium of the acoustic vibrations from the outlet opening to the mouth of the resonator neck tube.
  • a direction is designated, which points from the outlet opening into the channel and in the direction of the mouth of the resonator neck tubes.
  • the speed of a scavenging air through the hot gas side outlet of the resonator neck tubes can be chosen to be substantially lower, or the scavenging air through the resonator neck tube can be dispensed with altogether, since the speed of the acoustic fluctuations in the resonator neck is eliminated.
  • Tubes is decoupled from the outlet opening into a chamber to be damped. With chamber here is the case of a
  • Combustion chamber or the like in which a volume is enclosed with vibrations to be damped.
  • the hot gas intake into the at least one resonator neck tube is thus prevented or mitigated by the application of the at least one channel with cooling fluid.
  • the performance of the Helmholtz resonator - i. how strong the resonator is able to attenuate - is no longer impaired in this way.
  • Both the opening into a channel resonator neck tubes with the channel and the channel with a chamber wall may be formed, for example, in whole or in part in one piece.
  • chamber wall here is the case of a combustion chamber or the like referred to, in which a volume is enclosed with vibrations to be damped.
  • the channel is designed such that acoustic vibrations can be coupled into the outlet opening. That is, at least in a frequency band propagate to the outlet opening acoustic vibrations at least partially in the channel.
  • the channel can be arranged on or in a gas turbine such that at least one frequency band of the acoustic oscillations of a fluid flow flowing through a burner plenum and a combustion chamber can propagate to the outlet opening of the channel.
  • the channel of the damping device according to the invention for example, with its at least one outlet opening open directly into the combustion chamber or in the Brennerplenum.
  • the channel is different from the Brennerplenum.
  • the channel does not have to be acoustically permeable to all the frequencies that build up inside the gas turbine. It is sufficient if it is acoustically permeable in a suitable frequency band and in this respect is tuned with the Helmholtz resonator in a suitable manner.
  • An advantageous embodiment of the invention can provide that at least one channel is designed as a scavenging air channel with at least one inlet opening and at least one outlet opening, so that the scavenging air channel can be flowed through by scavenging air.
  • the loading of the channel takes place in this embodiment of the invention with purge air, which is passed through the channel.
  • the purge air may be, for example, compressor air.
  • the amount of purge air, which is consumed here, can be chosen to be much lower than that of the purged with rinsing Helmholtz resonators according to the prior art. In addition, this scavenging air no longer affects the performance of the Helmholtz resonator.
  • At least one channel of the damping device is at least partially flowed around by cooling fluid.
  • This embodiment of the invention has the advantage that the cooling fluid - eg compressor air - guesser combustion is available.
  • the channel can partially outside an inner combustion chamber housing by a
  • the channel could also be flushed with purge air in order to increase the cooling effect.
  • An advantageous embodiment of the invention can provide that the channel is at least partially surrounded by the resonator housing.
  • the resonator housing may have an annular cross-section.
  • Resonator neck tube inside the resonator housing opens into the channel.
  • the optionally provided with an inlet opening of the channel and the at least one outlet opening of the channel can be flush with the resonator housing in this embodiment of the invention.
  • the channel could also extend in another way through the resonator housing.
  • the channel may protrude from the resonator housing.
  • the resonator neck tubes can be
  • the resonator neck tubes can also be configured otherwise, for example, be screwed into the channel, so that the damping frequency of
  • Helmholtz resonator can easily be changed by replacing the resonator neck tubes.
  • the channel jacket of the channel can be referred to in the invention with channel wall.
  • At least one resonator neck tube is formed by perforation of the channel jacket of a channel.
  • This embodiment of the invention has particularly low manufacturing costs.
  • the resonator housing is cylindrical and surrounds a channel coaxially at least in sections.
  • This symmetrical design of the damping device can be particularly easily arranged on a gas turbine.
  • the height of the cylindrical resonator housing corresponds to 20-150% of the cylinder diameter of the resonator housing.
  • the height of the cylindrical resonator housing can in this case essentially correspond to the height of the cuboid resonators in the prior art.
  • the length of the coaxial in the surrounding channel opening resonator neck tubes is given by the dimensions of the resonator housing in limits.
  • This embodiment of the invention is particularly suitable for damping tube combustion chamber in which high-frequency thermoacoustic combustion vibrations can form.
  • the channel may be a cylindrical tube.
  • This embodiment of the channel is particularly easy to produce or has low manufacturing costs as a standard component.
  • the resonator neck tubes opening into the channel can, for example, discharge into this channel uniformly distributed over a section of the tube. But you could also, for example, only on one side of the tube along a in Open longitudinally of the tube running path in the channel.
  • Resonator neck tubes corresponds.
  • the acoustic permeability of the channel is adapted in this way particularly advantageous to the Helmholtz resonator.
  • a further advantageous embodiment of the invention can provide that the resonator housing is designed to rest with a housing wall of the resonator housing on a cold side of a chamber wall or to be integrally formed therewith, the chamber wall enclosing a volume with vibrations to be damped.
  • cooling air bores arranged at an angle can be introduced into the resonator housing such that an impingement cooling of the hot gas side housing wall is made possible.
  • a further advantageous embodiment of the invention can provide that the channel runs downstream of the at least one mouth of the opening into the channel Resonatorhals tubes outside the resonator housing, so that the damper tion device leaving a distance between the resonator housing and a chamber wall with an end of the channel on the chamber wall can be arranged, wherein the chamber wall enclosing a volume with vibrations to be damped.
  • This embodiment has the advantage that the channel can be cooled by means of compressor air flowing past. In this sense, the channel is at least partially flowed around with cooling fluid.
  • the embodiment has the further advantage that the impingement cooling of the housing wall of the resonator housing pointing in the direction of the hot side can be far smaller. It could be omitted altogether. Due to the spacing, the resonator housing can also by means of flowing past
  • Compressor air continues to be available for combustion.
  • it can further be provided that the
  • Damping device can be arranged detachably on the chamber wall.
  • the channel may have a thread in the region of the outlet opening, so that the channel can be screwed into an opening of the chamber wall.
  • the resonator housing for exchange with another
  • Resonator housing detachably connected to the channel.
  • a further object of the invention is to specify a gas turbine with at least one combustion chamber and at least one damping device of the type mentioned at the outset, which has a particularly effective damping of thermoacoustic
  • the damping device is designed according to one of claims 1 to 14. It can also be considered advantageous that the damping device is arranged substantially at the level of a combustion zone on a combustion chamber housing of the combustion chamber.
  • the damping device is arranged close to the acoustic source of the thermoacoustic oscillations. This leads to a further increase of the damping effect.
  • the resonator housing can surround a combustion chamber housing of the combustion chamber in an annular manner.
  • the average cross-sectional area of the channel between the outlet opening and the mouth region of the resonator neck tubes may be 2 to 10 times the sum of the cross-sectional areas of the resonator neck tubes connecting the channel to the resonant volume.
  • the channel will have a constant cross-section on this section so that this constant area can be used for the condition.
  • the channel does not behave as a resonator neck of the Helmholtz resonator and also has dimensions that allow for effective cooling.
  • the criterion is to be applied to at least one of the Helmholtz resonators, which is fluidically connected to the channel via the at least one resonator neck tube.
  • the channel is designed as a purge air channel with at least one of the resonator neck tubes different inlet opening and at least one outlet opening such that at least a portion of the purge air channel flowing through the cooling air omitting the resonant volume in the at least one Inlet opening and into the channel into conductive and can be conducted through the channel.
  • the channel may extend at least upstream of the outlet opening and upstream of the junction of the at least one resonator neck tube at least partially outside of the resonator housing and in this area at least partially flowed around by cooling air.
  • the damping device outside a combustion chamber and leaving a distance between the resonator housing and a combustion chamber wall with the at least one outlet opening comprehensive end of the channel can be arranged on the combustion chamber wall, so that the channel at least in sections can be flowed around by a compressor air stream flowing past the combustion chamber.
  • the cross section of the at least one inlet opening is smaller than the cross section of the scavenging air channel in the region of the inlet opening.
  • all opening into the purge air channel resonator neck tubes may have a smaller cross-section than the channel.
  • the channel may be substantially closed except for the at least one resonator neck tube and the at least one outlet opening.
  • the channel is thus primarily cooled by flowing around at least one channel section which can be arranged in the cooling air flow. If purge air is passed through the tubes at all, this amount can be reduced compared to the prior art.
  • Another object of the invention is to specify a method for damping thermoacoustic oscillations, in which at least one Helmholtz resonator dampens the vibrations and in this case the vibrations to be damped in at least one resonator neck of the Helmholtz resonator
  • the object is achieved in such a method in that the vibrations are first introduced into a channel and spread while cooling their transmission medium in this upstream and upstream in the opening resonator neck of the Helmholtz resonator
  • the transmission medium by means of
  • Rinsing air are cooled, so that the vibrations are first introduced into a purging air channel flushed opposite to its direction of propagation and upstream in the in the
  • Rinsing air channel opening resonator neck of the Helmholtz resonator are coupled.
  • the purge air may be compressor air.
  • the transmission medium can be cooled by flowing around the channel with a cooling fluid.
  • the channel can be additionally rinsed with purge air to increase the cooling effect.
  • sufficient cooling of the transmission medium can also be effected exclusively by means of the flow around the channel.
  • FIG. 2 shows schematically a first embodiment of a damping device according to the invention in one
  • FIG. 5 shows schematically a third embodiment of the damping device according to the invention in one
  • FIG. 6 shows a detail of a combustion chamber according to the invention with a damping device according to a fourth embodiment in a longitudinal section.
  • FIG. 1 shows a sectional view of a gas turbine 1 according to the prior art in a schematically simplified representation.
  • the gas turbine 1 has in its interior a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
  • a turbine runner which is also referred to as a turbine runner.
  • an intake housing 6 a compressor 8
  • a combustion system 9 with a number of tube combustion chambers 10, each comprising a burner assembly 11 and a housing 12, a turbine 14 and an exhaust housing 15th
  • the combustion system 9 communicates with an annular hot gas duct, for example.
  • a plurality of successively connected turbine stages form the turbine 14.
  • Each turbine stage is formed of blade rings.
  • a row formed of rotor blades 18 follows in the hot runner of a row formed by vanes 17.
  • the guide vanes 17 are fastened to an inner housing of a stator 19, whereas the rotor blades 18 of a row are attached to the rotor 3, for example by means of a turbine disk.
  • Coupled to the rotor 3 is, for example, a generator (not shown).
  • air is sucked in and compressed by the compressor 8 through the intake housing 6.
  • the compressed air provided at the turbine-side end of the compressor 8 is led to the combustion system 9 where it is mixed with a fuel in the area of the burner assembly 11.
  • the mixture is then burned by means of the burner assembly 11 to form a working gas stream in the combustion system 9.
  • the working gas stream flows along the hot gas channel past the guide vanes 17 and the rotor blades 18.
  • the working gas stream relaxes in a pulse-transmitting manner, so that the rotor blades 18 drive the rotor 3 and this drives the generator (not shown) coupled to it.
  • 2 shows a first embodiment of a damping device 22 according to the invention in a schematic representation in a longitudinal section.
  • the damping device 22 comprises a Helmholtz resonator 23 and a channel in the form of a purge air channel 24 with a channel casing 25.
  • the Helmholtz resonator 23 has a cylindrical resonator housing 27, wherein the cylindrical purge air channel 24 through the resonator housing 27th extends through and is surrounded by the resonator housing 27 coaxially.
  • the resonator housing 27 encloses the resonance volume 30 of the Helmholtz resonator.
  • Resonator neck tubes 28 open into the interior of the resonator housing 27 in the purge air channel 24 a.
  • the resonator neck tubes 28 are arranged such that they have hot gas side - ie with their hot gas side outlet 33 downstream of an inlet opening 34 of the purge air channel and upstream of an outlet opening 35 of the
  • the resonator housing 27 comprises a housing wall 38, which is formed integrally with a chamber wall 39.
  • the chamber wall 39 in this case encloses a volume with vibrations to be damped, which is encompassed by the environment 32 of the Helmholtz resonator to be damped.
  • a combustion chamber housing In the illustrated chamber wall 39 is a combustion chamber housing, wherein in the combustion chamber, a hot working gas stream 40 flows.
  • the hot working gas flow 40 corresponds to a fluid flow passing through a burner plenum and a combustion chamber, which is referred to as the hot working gas flow 40 in the section of the combustion chamber.
  • cooling channels 41 may be introduced in the resonator housing 27.
  • thermoacoustic oscillations in the combustion chamber arising during the combustion couple through the resonator neck tubes 28 into the Helmholtz resonator 23 and are damped in the latter.
  • a hot gas intake is reliably avoided.
  • the speed of the purging air in the purging air channel 24 does not influence the speed of the coupled acoustic oscillations in the resonator neck tubes 28, so that the performance of the Helmholtz resonator 23 - ie its damping effect - is unaffected by the speed the exiting from the outlet opening 35 scavenging air.
  • the hot gas end of the scavenging air channel 24 is integrally formed with the chamber wall 39 in the region of the outlet opening 35.
  • the very compact construction of the damping device 22 can be further simplified in that the resonator neck tubes 28 are formed by means of perforation of the channel wall 25 of the purging air channel 24.
  • the height 45 of the cylindrical resonator housing 27 corresponds to 20-150% of the cylinder diameter 46 of the resonator housing 27.
  • Purge air channel 24 may be connected.
  • FIG. 3 shows the damping device 22 shown in FIG. 2 from a plan view.
  • the cylindrical resonator Gate housing 27 has on its upper side the inlet opening 34 of the scavenging air channel 24.
  • the course of the channel sheathing 25 of the purge air channel is indicated by dash-dotted lines.
  • FIG. 4 shows a second exemplary embodiment of a damping device 50 according to the invention.
  • This has a smaller cross-section of the outlet opening 52 of the purge air duct 53 than the embodiment shown in FIG.
  • the cross-sectional area of the outlet opening 52 of the scavenging air channel corresponds to 1 to 2 times the total cross-sectional area of the resonator neck tubes 28 opening into the scavenging air channel 53. This allows reliable avoidance of hot gas intake with low consumption of
  • FIG. 5 shows a third exemplary embodiment of a damping device 56 according to the invention with a Helmholtz resonator 58 and a channel 60.
  • the channel 60 runs downstream of the at least one confluence of the resonator neck tubes 28 opening into the purge air channel 60 outside of the resonator housing 27.
  • the damping device 56 is leaving a distance between the resonator housing 27 and a chamber wall 39 with an end 62 of the channel 60 on the chamber wall
  • the Helmholtz resonator can be cooled by, for example, 64 flowing compressor air.
  • the additionally arranged in the resonator housing 27 cooling channels 41 can in this way.
  • the damping device 56 may be releasably attached to the chamber wall 39. For example, by means of a thread formed on the channel 60 in the region of the end 62.
  • FIG. 6 shows a section of a gas turbine combustion chamber 65 with a damping device 66 according to the invention according to a fourth exemplary embodiment in a longitudinal direction. cut.
  • the figure is a simplified, schematic representation of the combustion chamber.
  • the gas turbine combustion chamber 65 comprises a rotationally symmetrical combustion chamber housing 68, at whose upstream end a pilot burner 70 and two main burners 71, 72 are arranged.
  • the damping device 66 is arranged at the level of a combustion zone 74 on the combustion chamber 65.
  • the resonator housing 76 of the damping device 66 extends annularly around the combustion chamber housing 68, wherein a plurality of channels 77a, 77b carry the resonator housing 76.
  • the channels 77a, 77b are flowed around by compressor air and thus acted upon by adefuid.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)

Abstract

L'invention concerne un dispositif d'amortissement (50) qui est destiné à une turbine à gaz et qui comporte • - au moins un résonateur de Helmholtz (23) et • - au moins un canal (53), • - le résonateur de Helmholtz comportant une bouteille de résonateur (27) un au moins col de résonateur (28), la bouteille de résonateur (27) enfermant un volume de résonance (30) du résonateur de Helmholtz (23), le col de résonateur (28) permettant d' injecter des vibrations acoustiques dans ledit volume. Le dispositif d'amortissement selon l'invention permet d'amortir des vibrations thermoacoustiques de manière particulièrement efficace. A cet effet, le canal (53) est pourvu d'une enveloppe de canal et d'au moins une sortie (52). Des vibrations acoustiques, produites par un écoulement fluidique traversant un plénum de brûleur et une chambre de combustion, peuvent être injectées dans ladite sortie. Le canal peut être soumis à l'effet d'un fluide de refroidissement et, sur le côté des gaz chauds, l'au moins un col de résonateur débouche dans un tel canal en amont de l'au moins une sortie.
EP14707733.3A 2013-02-28 2014-02-28 Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques Withdrawn EP2962039A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14707733.3A EP2962039A1 (fr) 2013-02-28 2014-02-28 Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP13157106 2013-02-28
EP14707733.3A EP2962039A1 (fr) 2013-02-28 2014-02-28 Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques
PCT/EP2014/053921 WO2014131876A1 (fr) 2013-02-28 2014-02-28 Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques

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US (1) US20160003162A1 (fr)
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CN105008805A (zh) 2015-10-28
WO2014131876A1 (fr) 2014-09-04
US20160003162A1 (en) 2016-01-07

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