EP2500648B1 - Gas turbine combustion chamber - Google Patents

Gas turbine combustion chamber Download PDF

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Publication number
EP2500648B1
EP2500648B1 EP11158268.0A EP11158268A EP2500648B1 EP 2500648 B1 EP2500648 B1 EP 2500648B1 EP 11158268 A EP11158268 A EP 11158268A EP 2500648 B1 EP2500648 B1 EP 2500648B1
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EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
gas turbine
resonance chambers
corrugated component
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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.)
Not-in-force
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EP11158268.0A
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German (de)
French (fr)
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EP2500648A1 (en
Inventor
Andreas Böttcher
Olga Deiss
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Siemens AG
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Siemens AG
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Priority to EP11158268.0A priority Critical patent/EP2500648B1/en
Priority to ES11158268T priority patent/ES2427440T3/en
Priority to US13/414,051 priority patent/US8464536B2/en
Priority to RU2012109927/06A priority patent/RU2012109927A/en
Priority to CN201210069388.1A priority patent/CN102679396B/en
Publication of EP2500648A1 publication Critical patent/EP2500648A1/en
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Publication of EP2500648B1 publication Critical patent/EP2500648B1/en
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    • 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
    • F23D—BURNERS
    • F23D2210/00—Noise abatement
    • 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 gas turbine combustion chamber, with a combustion chamber interior and a combustion chamber wall, which has a substantially rotationally symmetrical cross section.
  • 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 combustors 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.
  • thermoacoustic oscillations are therefore in the prior art, for example, Helmholtz resonators for Damping used to dampen the amplitude of vibrations of certain frequencies.
  • Helmholtz resonators attenuate depending on the cross-sectional area of the connecting tube and the resonator volume, in particular the amplitude of vibrations, with the Helmholtz frequency.
  • These Helmholtz resonators are mostly small boxes, which are individually welded onto the combustion chamber wall of the gas turbine. However, this is very complicated and expensive. In addition, these small boxes and their weld have a short life.
  • a gas turbine combustion chamber having a combustion chamber interior and a combustion chamber wall which has a substantially rotationally symmetrical cross section.
  • a corrugated component is arranged over the entire cross-sectional circumference of the combustion chamber wall, which forms a plurality of separate resonance chambers with the combustion chamber wall. Openings are introduced in the combustion chamber wall such that in each case a fluid connection between the combustion chamber interior and one of the resonance chambers is provided.
  • the corrugated member has two locking rings which are connected to the combustion chamber wall to seal the resonance spaces.
  • the resonance chambers are thus also designed as cavity resonators. With such a gas turbine combustor, frequencies can be easily damped.
  • Such a corrugated component can also be easily and inexpensively mounted.
  • the corrugated component can be attached over the entire length of the combustion chamber wall. As a result, an efficient damping on the entire length of the combustion chamber wall is possible.
  • the corrugated member may be mounted only on a longitudinal portion of the combustion chamber wall.
  • At least two of the openings present in the combustion chamber wall have a different cross section, wherein each of the at least two openings has a separate fluid connection to at least two separate resonance chambers. This can very easily be used to attenuate different frequencies, such as e.g. when changing from full to partial load occur.
  • the corrugated component bores.
  • cooling air can be introduced into the resonance chamber. This cools both the corrugated member and the combustion chamber wall, e.g. by impingement cooling.
  • the corrugated component has at least two wave troughs.
  • the corrugated component is welded or soldered in these wave troughs with the combustion chamber wall. This ensures in a simple manner that the resonance chambers are separated even with thermal expansion of the corrugated component and / or thermal expansion of the combustion chamber wall. In addition, this represents a simple heat-resistant attachment of the corrugated component to the combustion chamber wall.
  • At least two separate resonance chambers have different volumes. This also different frequencies can be attenuated.
  • FIG. 1 shows in sections a gas turbine combustor 1 according to the invention.
  • the gas turbine combustor 1 has a combustion chamber interior and a combustion chamber wall 2 with a substantially rotationally symmetrical cross section.
  • a corrugated component 3 is arranged over the entire circumference of the combustion chamber wall 2.
  • the corrugated component 3 can be a sheet metal.
  • the component 3 forms with the combustion chamber wall 2 a plurality of separate resonance chambers 5 (FIG. Fig. 2 ) out. Openings 4 ( Fig. 3 ) are introduced in the combustion chamber wall 2 such that in each case a fluid connection between the combustion chamber interior and one of the resonance chambers 5 (FIG. Fig.
  • Each resonance chamber 5 ( Fig. 2 ) is therefore at least one opening 4 ( Fig. 3 ).
  • the corrugated component 3 has two closure rings 6, which are connected to the combustion chamber wall 2, around the resonance chambers 5 (FIG. Fig. 2 ) seal.
  • the two locking rings 6 represent, as it were, a cover of the corrugated component 3, which is otherwise open at both ends. This means that the resonance spaces 5 (FIG. Fig. 2 ) are sealed so to speak by these locking rings 6.
  • the locking rings 6 may be welded or soldered to the combustion chamber wall 2. Likewise, they are additionally soldered or welded to the corrugated component 3.
  • the resonance chambers 5 ( Fig. 2 ) may have different volumes. As a result, different frequencies can be damped.
  • holes 7 may be mounted to realize cooling of the corrugated member 3 but also the combustion chamber wall 2 by means of cooling air through these holes 7.
  • the cooling air passes through the bores 7 into the resonance chambers 5 (FIG. Fig. 2 ) and cools the combustion chamber wall 2, for example by means of impingement cooling.
  • the holes 7 are therefore above the resonance chambers 5 ( Fig. 2 ) appropriate.
  • FIG. 2 shows in sections a cross section of a gas turbine combustor 1 according to the invention with the corrugated component 3.
  • the corrugated component 3 has wave troughs 8. At these wave troughs 8, the corrugated component 3 rests directly on the combustion chamber wall 2.
  • the corrugated component 3 welded to the combustion chamber wall 2 or soldered. This ensures that no fluid connection between the resonance chambers 5 takes place.
  • the welding or soldering can be provided over the entire length of the corrugated component 3.
  • FIG. 3 shows in sections a longitudinal section of a gas turbine combustor 1 according to the invention with corrugated component 3.
  • the existing in the combustion chamber wall 2 openings 4 to at least two separate resonance chambers 5 may have a different cross-section. Thus, different frequencies can be damped.
  • the corrugated member 3 may be mounted on the entire length of the combustion chamber wall 2, or only on a part of the length of the combustion chamber wall 2.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

The chamber (1) has corrugated component (3) arranged on side of combustion chamber wall (2) facing away from combustion chamber interior over entire cross-sectional circumference of combustion chamber wall. The corrugated component has several separate resonance chambers (5) provided in the combustion chamber wall in combination with combustion chamber wall, such that fluidic connection is established between combustion chamber interior and resonance chambers. The corrugated component has two locking rings which are connected to combustion chamber wall to seal off resonance chambers.

Description

Die Erfindung betrifft eine Gasturbinenbrennkammer, mit einem Brennkammerinneren und einer Brennkammerwand, welche einen im Wesentlichen rotationssymmetrischen Querschnitt aufweist.The invention relates to a gas turbine combustion chamber, with a combustion chamber interior and a combustion chamber wall, which has a substantially rotationally symmetrical cross section.

Eine Gasturbinenanlage umfasst im einfachsten Fall einen Verdichter, eine Brennkammer sowie eine Turbine. Im Verdichter erfolgt ein Verdichten von angesaugter Luft, welcher anschließend ein Brennstoff beigemischt wird. In der Brennkammer erfolgt eine Verbrennung des Gemisches, wobei die Verbrennungsabgase der Turbine zugeführt werden, von der den Verbrennungsabgasen Energie entzogen und in mechanische Energie umgesetzt wird.A gas turbine plant comprises in the simplest case a compressor, a combustion chamber and a turbine. In the compressor there is a compression of sucked air, which is then admixed with a fuel. In 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.

Schwankungen in der Brennstoffqualität und sonstige thermische oder akustische Störungen führen jedoch zu Schwankungen in der freigesetzten Wärmemenge. Dabei liegt eine Wechselwirkung von akustischen und thermischen Störungen vor, die sich aufschwingen können. Derartige thermoakustische Schwingungen in den Brennkammern von Gasturbinen - oder auch Strömungsmaschinen im Allgemeinen - stellen ein Problem bei dem Entwurf und bei dem Betrieb von neuen Brennkammern, Brennkammerteilen und Brennern für derartige Strömungsmaschinen dar.Fluctuations in fuel quality and other thermal or acoustic disturbances, however, lead to fluctuations in the amount of heat released. There is an interaction of acoustic and thermal disturbances, which can oscillate. Such thermoacoustic oscillations in the combustors 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.

Um Schadstoffemissionen zu verringern, wird in modernen Anlagen der Kühlmassenstrom verringert. Dadurch wird auch die akustische Dämpfung verringert, so dass thermoakustischen Schwingungen zunehmen können. Dabei kann es zu einer sich aufschaukelnden Wechselwirkung zwischen thermischen und akustischen Störungen kommen, die hohe Belastungen der Brennkammer und steigende Emissionen verursachen können.In order to reduce pollutant emissions, the cooling mass flow is reduced in modern plants. As a result, the acoustic damping is reduced, so that 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.

Zur Verringerung von thermoakustischen Schwingungen werden deshalb im Stand der Technik, z.B. Helmholtz-Resonatoren zur Dämpfung eingesetzt, die die Amplitude von Schwingungen bestimmter Frequenzen dämpfen.To reduce thermoacoustic oscillations are therefore in the prior art, for example, Helmholtz resonators for Damping used to dampen the amplitude of vibrations of certain frequencies.

Eine solche Anordnung ist in EP 1 510 752 A2 beschrieben.Such an arrangement is in EP 1 510 752 A2 described.

Derartige Helmholtz-Resonatoren dämpfen in Abhängigkeit von der Querschnittsfläche des Verbindungsrohres und vom Resonatorvolumen, insbesondere die Amplitude von Schwingungen, mit der Helmholtzfrequenz. Diese Helmholtz-Resonatoren sind zumeist kleine Boxen, welche auf der Brennkammerwand der Gasturbine einzeln aufgeschweißt werden. Dies ist jedoch sehr aufwendig und teuer. Zudem weisen diese kleinen Boxen und deren Schweißnaht eine nur geringe Lebensdauer auf.Such Helmholtz resonators attenuate depending on the cross-sectional area of the connecting tube and the resonator volume, in particular the amplitude of vibrations, with the Helmholtz frequency. These Helmholtz resonators are mostly small boxes, which are individually welded onto the combustion chamber wall of the gas turbine. However, this is very complicated and expensive. In addition, these small boxes and their weld have a short life.

Es ist daher die Aufgabe der vorliegenden Erfindung, eine Gasturbinenbrennkammer anzugeben, welche die obigen Nachteile vermeidet.It is therefore the object of the present invention to provide a gas turbine combustor which avoids the above disadvantages.

Erfindungsgemäß wird diese Aufgabe gelöst durch eine Gasturbinenbrennkammer, mit einem Brennkammerinneren und einer Brennkammerwand, welche einen im Wesentlichen rotationssymmetrischen Querschnitt aufweist. Auf von einer dem Brennkammerinneren abgewandten Seite der Brennkammerwand ist über den gesamten Querschnittsumfang der Brennkammerwand ein gewelltes Bauteil angeordnet, welches mit der Brennkammerwand mehrere separate Resonanzräume ausbildet. Öffnungen sind in der Brennkammerwand derart eingebracht, dass jeweils eine Fluidverbindung zwischen dem Brennkammerinneren und einer der Resonanzräume gegeben ist. Das gewellte Bauteil weist zwei Verschlussringe auf, die mit der Brennkammerwand verbunden sind, um die Resonanzräume abzudichten. Die Resonanzräume sind damit auch als Hohlraumresonatoren ausgebildet. Mit einer solchen Gasturbinenbrennkammer können Frequenzen einfach gedämpft werden. Ein solches gewelltes Bauteil kann auch einfach und kostengünstig aufmontiert werden. Das gewellte Bauteil kann dabei auf der gesamten Länge der Brennkammerwand angebracht sein. Dadurch ist eine effiziente Dämpfung auf der gesamten Länge der Brennkammerwand möglich. Alternativ kann jedoch das gewellte Bauteil nur auf einen Längenabschnitt der Brennkammerwand angebracht sein.According to the invention, this object is achieved by a gas turbine combustion chamber having a combustion chamber interior and a combustion chamber wall which has a substantially rotationally symmetrical cross section. On a side facing away from the combustion chamber interior side of the combustion chamber wall, a corrugated component is arranged over the entire cross-sectional circumference of the combustion chamber wall, which forms a plurality of separate resonance chambers with the combustion chamber wall. Openings are introduced in the combustion chamber wall such that in each case a fluid connection between the combustion chamber interior and one of the resonance chambers is provided. The corrugated member has two locking rings which are connected to the combustion chamber wall to seal the resonance spaces. The resonance chambers are thus also designed as cavity resonators. With such a gas turbine combustor, frequencies can be easily damped. Such a corrugated component can also be easily and inexpensively mounted. The corrugated component can be attached over the entire length of the combustion chamber wall. As a result, an efficient damping on the entire length of the combustion chamber wall is possible. Alternatively, however, the corrugated member may be mounted only on a longitudinal portion of the combustion chamber wall.

Vorteilhafterweise weisen zumindest zwei der in der Brennkammerwand vorhandenen Öffnungen einen unterschiedlichen Querschnitt auf, wobei jede der zumindest zwei Öffnungen eine separate Fluidverbindung zu zumindest zwei separaten Resonanzräumen aufweist. Damit können sehr einfach unterschiedliche Frequenzen gedämpft werden, wie sie z.B. beim Wechsel von Voll- zu Teillast auftreten.Advantageously, at least two of the openings present in the combustion chamber wall have a different cross section, wherein each of the at least two openings has a separate fluid connection to at least two separate resonance chambers. This can very easily be used to attenuate different frequencies, such as e.g. when changing from full to partial load occur.

Vorteilhaftweise weist das gewellte Bauteil Bohrungen auf. Dadurch kann Kühlluft in den Resonanzraum eingebracht werden. Diese kühlt sowohl das gewellte Bauteil als auch die Brennkammerwand, z.B. mittels Prallkühlung.Advantageously, the corrugated component bores. As a result, cooling air can be introduced into the resonance chamber. This cools both the corrugated member and the combustion chamber wall, e.g. by impingement cooling.

In vorteilhafter Ausgestaltung weist das gewellte Bauteil zumindest zwei Wellentäler auf. Das gewellte Bauteil ist in diesen Wellentälern mit der Brennkammerwand verschweißt oder verlötet. Dadurch wird auf einfache Art und Weise sichergestellt, dass die Resonanzräume auch bei thermischer Ausdehnung des gewellten Bauteils und bzw. oder thermischer Ausdehnung der Brennkammerwand separiert sind. Zudem stellt dies eine einfache hitzebeständige Befestigung des gewellten Bauteils an der Brennkammerwand dar.In an advantageous embodiment, the corrugated component has at least two wave troughs. The corrugated component is welded or soldered in these wave troughs with the combustion chamber wall. This ensures in a simple manner that the resonance chambers are separated even with thermal expansion of the corrugated component and / or thermal expansion of the combustion chamber wall. In addition, this represents a simple heat-resistant attachment of the corrugated component to the combustion chamber wall.

Vorteilhafterweise weisen zumindest zwei separate Resonanzräume unterschiedliche Volumen auf. Damit können ebenfalls unterschiedliche Frequenzen gedämpft werden.Advantageously, at least two separate resonance chambers have different volumes. This also different frequencies can be attenuated.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren 1-3.

Figur 1
zeigt abschnittweise eine erfindungsgemäße Gasturbinenbrennkammer mit gewelltem Bauteil.
Figur 2
zeigt abschnittsweise einen Querschnitt einer erfindungsgemäßen Gasturbinenbrennkammer mit gewelltem Bauteil.
Figur 3
zeigt abschnittsweise einen Längsschnitt einer erfindungsgemäßen Gasturbinenbrennkammer mit gewelltem Bauteil.
Further features, characteristics and advantages of the present invention will become apparent from the following description of embodiments with reference to the accompanying Figures 1-3 ,
FIG. 1
shows sections of a gas turbine combustor according to the invention with a corrugated component.
FIG. 2
shows in sections a cross section of a gas turbine combustor according to the invention with a corrugated component.
FIG. 3
shows in sections a longitudinal section of a gas turbine combustor according to the invention with a corrugated component.

Die Figur 1 zeigt abschnittweise eine erfindungsgemäße Gasturbinenbrennkammer 1. Zudem hat die Gasturbinenbrennkammer 1 ein Brennkammerinneres und eine Brennkammerwand 2 mit einen im Wesentlichen rotationssymmetrischem Querschnitt. Auf der von einer dem Brennkammerinneren abgewandten Seite der Brennkammerwand 2 ist über den gesamten Umfang der Brennkammerwand 2 ein gewelltes Bauteil 3 angeordnet. Das gewellte Bauteil 3 kann dabei ein Blech sein. Das Bauteil 3 bildet mit der Brennkammerwand 2 mehrere separate Resonanzräume 5 (Fig. 2) aus. Öffnungen 4 (Fig. 3) sind in der Brennkammerwand 2 derart eingebracht, dass jeweils eine Fluidverbindung zwischen dem Brennkammerinneren und einer der Resonanzräume 5 (Fig. 2) gegeben ist. Jedem Resonanzraum 5 (Fig. 2) ist daher mindestens eine Öffnung 4 (Fig. 3) zugeordnet. Das gewellte Bauteil 3 weist zwei Verschlussringe 6 auf, die mit der Brennkammerwand 2 verbunden sind, um die Resonanzräume 5 (Fig. 2) abzudichten. Die zwei Verschlussringe 6 stellen quasi eine Abdeckung des ansonsten an beiden Enden offenen, gewellten Bauteils 3 dar. Dies bedeutet, dass die Resonanzräume 5 (Fig. 2) sozusagen durch diese Verschlussringe 6 abgedichtet werden. Die Verschlussringe 6 können auf der Brennkammerwand 2 angeschweißt oder aufgelötet sein. Ebenso werden sie zusätzlich mit dem gewellten Bauteil 3 verlötet oder verschweißt. Die Resonanzräume 5 (Fig. 2) können unterschiedliches Volumen aufweisen. Dadurch können unterschiedliche Frequenzen gedämpft werden. In dem gewellten Bauteil 3 können Bohrungen 7 angebracht sein, um eine Kühlung des gewellten Bauteils 3 aber auch der Brennkammerwand 2 mittels Kühlluft durch diese Bohrungen 7 zu realisieren. Die Kühlluft tritt durch die Bohrungen 7 in die Resonanzräume 5 (Fig. 2) ein und kühlt die Brennkammerwand 2, z.B. mittels Prallkühlung. Die Bohrungen 7 sind daher oberhalb der Resonanzräume 5 (Fig. 2) angebracht.The FIG. 1 shows in sections a gas turbine combustor 1 according to the invention. In addition, the gas turbine combustor 1 has a combustion chamber interior and a combustion chamber wall 2 with a substantially rotationally symmetrical cross section. On the side facing away from the combustion chamber interior side of the combustion chamber wall 2, a corrugated component 3 is arranged over the entire circumference of the combustion chamber wall 2. The corrugated component 3 can be a sheet metal. The component 3 forms with the combustion chamber wall 2 a plurality of separate resonance chambers 5 (FIG. Fig. 2 ) out. Openings 4 ( Fig. 3 ) are introduced in the combustion chamber wall 2 such that in each case a fluid connection between the combustion chamber interior and one of the resonance chambers 5 (FIG. Fig. 2 ) given is. Each resonance chamber 5 ( Fig. 2 ) is therefore at least one opening 4 ( Fig. 3 ). The corrugated component 3 has two closure rings 6, which are connected to the combustion chamber wall 2, around the resonance chambers 5 (FIG. Fig. 2 ) seal. The two locking rings 6 represent, as it were, a cover of the corrugated component 3, which is otherwise open at both ends. This means that the resonance spaces 5 (FIG. Fig. 2 ) are sealed so to speak by these locking rings 6. The locking rings 6 may be welded or soldered to the combustion chamber wall 2. Likewise, they are additionally soldered or welded to the corrugated component 3. The resonance chambers 5 ( Fig. 2 ) may have different volumes. As a result, different frequencies can be damped. In the corrugated component 3 holes 7 may be mounted to realize cooling of the corrugated member 3 but also the combustion chamber wall 2 by means of cooling air through these holes 7. The cooling air passes through the bores 7 into the resonance chambers 5 (FIG. Fig. 2 ) and cools the combustion chamber wall 2, for example by means of impingement cooling. The holes 7 are therefore above the resonance chambers 5 ( Fig. 2 ) appropriate.

Figur 2 zeigt abschnittsweise einen Querschnitt einer erfindungsgemäßen Gasturbinenbrennkammer 1 mit dem gewellten Bauteil 3. Das gewellte Bauteil 3 weist Wellentäler 8 auf. An diesen Wellentälern 8 liegt das gewellte Bauteil 3 direkt auf der Brennkammerwand 2 auf. Bevorzugt wird in den Wellentälern 8, das gewellte Bauteil 3, auf die Brennkammerwand 2 geschweißt oder gelötet. Dadurch wird sichergestellt, dass keine Fluidverbindung zwischen den Resonanzräumen 5 stattfindet. Die Schweißung oder Lötung kann dabei auf der gesamten Länge des gewellten Bauteils 3 vorgesehen sein. Es kann aber auch ein anderes stoffschlüssiges oder formschlüssiges Verfahren angewendet werden. FIG. 2 shows in sections a cross section of a gas turbine combustor 1 according to the invention with the corrugated component 3. The corrugated component 3 has wave troughs 8. At these wave troughs 8, the corrugated component 3 rests directly on the combustion chamber wall 2. Preferably, in the troughs 8, the corrugated component 3, welded to the combustion chamber wall 2 or soldered. This ensures that no fluid connection between the resonance chambers 5 takes place. The welding or soldering can be provided over the entire length of the corrugated component 3. However, it is also possible to use another cohesive or positive-locking method.

Figur 3 zeigt abschnittsweise einen Längsschnitt einer erfindungsgemäßen Gasturbinenbrennkammer 1 mit gewelltem Bauteil 3. Die in der Brennkammerwand 2 vorhandenen Öffnungen 4 zu zumindest zwei separaten Resonanzräumen 5 (Fig. 2) können einen unterschiedlichen Querschnitt aufweisen. Somit können unterschiedliche Frequenzen gedämpft werden. Das gewellte Bauteil 3 kann auf der gesamten Länge der Brennkammerwand 2 angebracht werden, oder nur auf einem Teil der Länge der Brennkammerwand 2. FIG. 3 shows in sections a longitudinal section of a gas turbine combustor 1 according to the invention with corrugated component 3. The existing in the combustion chamber wall 2 openings 4 to at least two separate resonance chambers 5 (FIGS. Fig. 2 ) may have a different cross-section. Thus, different frequencies can be damped. The corrugated member 3 may be mounted on the entire length of the combustion chamber wall 2, or only on a part of the length of the combustion chamber wall 2.

Durch die erfindungsgemäße Gasturbine mit dem gewellten Bauteil 3 kann eine einfache Dämpfung von Frequenzen erzielt werden. Zudem weist ein solches gewelltes Bauteil 3, eine längere Lebensdauer als ein herkömmlicher Helmholtz-Resonator auf. Durch die verschiedenen Volumen der Resonanzräume 5 (Fig. 2) ist zudem eine einfache Dämpfung verschiedener Frequenzen möglich.By the gas turbine according to the invention with the corrugated component 3, a simple attenuation of frequencies can be achieved. In addition, such a corrugated component 3, has a longer life than a conventional Helmholtz resonator. Due to the different volumes of the resonance chambers 5 ( Fig. 2 ) is also a simple attenuation of different frequencies possible.

Claims (5)

  1. Gas turbine combustion chamber (1), comprising a combustion chamber interior and a combustion chamber wall (2) which has a substantially rotationally symmetrical cross-section (2),
    characterised in that on the side of the combustion chamber wall (2) facing away from the combustion chamber interior there is arranged over the entire cross-sectional circumference of the combustion chamber wall (2) a corrugated component (3) which, in combination with the combustion chamber wall (2), embodies a plurality of separate resonance chambers (5) and wherein openings (4) are incorporated in the combustion chamber wall (2) in such a way that a fluidic connection is established in each case between the combustion chamber interior and one of the resonance chambers (5) and wherein the corrugated component (3) has two locking rings (6) which are connected to the combustion chamber wall (2) in order to seal off the resonance chambers (5).
  2. Gas turbine combustion chamber (1) according to claim 1,
    characterised in that at least two of the openings (4) present in the combustion chamber wall (2) have a different cross-section, with each of the at least two openings (4) having a separate fluidic connection to at least two separate resonance chambers (5).
  3. Gas turbine combustion chamber (1) according to one of the preceding claims,
    characterised in that the corrugated component (3) has corrugation troughs (8) between the resonance chambers (5) and wherein the corrugated component (3) is welded and/or soldered to the combustion chamber wall (2) in said corrugation troughs (8).
  4. Gas turbine combustion chamber (1) according to one of the preceding claims,
    characterised in that the corrugated component (3) has drilled holes (7).
  5. Gas turbine combustion chamber (1) according to one of the preceding claims,
    characterised in that at least two separate resonance chambers (5) have different volumes.
EP11158268.0A 2011-03-15 2011-03-15 Gas turbine combustion chamber Not-in-force EP2500648B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP11158268.0A EP2500648B1 (en) 2011-03-15 2011-03-15 Gas turbine combustion chamber
ES11158268T ES2427440T3 (en) 2011-03-15 2011-03-15 Gas turbine combustion chamber
US13/414,051 US8464536B2 (en) 2011-03-15 2012-03-07 Gas turbine combustion chamber
RU2012109927/06A RU2012109927A (en) 2011-03-15 2012-03-14 GAS TURBINE COMBUSTION CHAMBER
CN201210069388.1A CN102679396B (en) 2011-03-15 2012-03-15 Gas turbine combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11158268.0A EP2500648B1 (en) 2011-03-15 2011-03-15 Gas turbine combustion chamber

Publications (2)

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EP2500648A1 EP2500648A1 (en) 2012-09-19
EP2500648B1 true EP2500648B1 (en) 2013-09-04

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EP11158268.0A Not-in-force EP2500648B1 (en) 2011-03-15 2011-03-15 Gas turbine combustion chamber

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US (1) US8464536B2 (en)
EP (1) EP2500648B1 (en)
CN (1) CN102679396B (en)
ES (1) ES2427440T3 (en)
RU (1) RU2012109927A (en)

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RU2530685C2 (en) * 2010-03-25 2014-10-10 Дженерал Электрик Компани Impact action structures for cooling systems
US8966903B2 (en) * 2011-08-17 2015-03-03 General Electric Company Combustor resonator with non-uniform resonator passages
EP2816288B1 (en) * 2013-05-24 2019-09-04 Ansaldo Energia IP UK Limited Combustion chamber for a gas turbine with a vibration damper
CN105157060A (en) * 2014-05-30 2015-12-16 胡晋青 Turbine combustion chamber
CN104676649A (en) * 2015-02-05 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Damping thermo-acoustic vibration acoustic flame tube
JP6815735B2 (en) * 2016-03-03 2021-01-20 三菱パワー株式会社 Audio equipment, gas turbine
CN106068054A (en) * 2016-05-24 2016-11-02 中国人民解放军装备学院 A kind of fluid-cooled gas Metastable atomic beam stream generation apparatus
JP7008722B2 (en) 2017-03-30 2022-01-25 シーメンス アクティエンゲゼルシャフト A system with a conduit arrangement for dual use of cooling fluid in the combustor section of a gas turbine engine
CN114811649B (en) * 2022-04-07 2024-05-10 中国联合重型燃气轮机技术有限公司 Combustion chamber and gas turbine with same

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Also Published As

Publication number Publication date
US20120234009A1 (en) 2012-09-20
CN102679396B (en) 2015-07-01
ES2427440T3 (en) 2013-10-30
CN102679396A (en) 2012-09-19
US8464536B2 (en) 2013-06-18
EP2500648A1 (en) 2012-09-19
RU2012109927A (en) 2013-09-20

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