EP2383515B1 - Combustion system for dampening such a combustion system - Google Patents

Combustion system for dampening such a combustion system Download PDF

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Publication number
EP2383515B1
EP2383515B1 EP20100161306 EP10161306A EP2383515B1 EP 2383515 B1 EP2383515 B1 EP 2383515B1 EP 20100161306 EP20100161306 EP 20100161306 EP 10161306 A EP10161306 A EP 10161306A EP 2383515 B1 EP2383515 B1 EP 2383515B1
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EP
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Prior art keywords
burner
head
combustion
combustion chamber
cap
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EP20100161306
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German (de)
French (fr)
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EP2383515A1 (en
Inventor
Sven Bethke
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Siemens AG
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Siemens AG
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23MCASINGS, 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
    • F23M20/00Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005Noise absorbing means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54Reverse-flow combustion chambers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Abstract

The burner system has two adjacent burners (7), where the former burner has a combustion chamber (6) and a head end. The latter burner has a fuel injection unit (55) and a fuel-air premix (56). Each burner has a cap with a cap side (150) and a cap upper side (170). Two burner-plenums (100) are provided with an acoustic connection (130). Independent claims are also included for the following: (1) a gas turbine with a compressor; and (2) a method for damping vibration of a burner system.

Description

  • Die Erfindung betrifft ein Brennersystem mit zumindest zwei benachbarten Brennern, von denen jeder zumindest eine Brennkammer und ein Kopfende aufweist, wobei letzteres zumindest eine Kraftstoffeinspritzung sowie eine Kraftstoff-Luft Vormischung umfasst, wobei jeder Brenner einen Hut mit einer Hutseite und einer Hutoberseite aufweist, wobei zumindest die Hutoberseite in Strömungsrichtung gesehen vor dem Kopfende angeordnet ist, wobei zwischen der Hutoberseite und dem Kopfende dadurch ein Brenner-Plenum ausgebildet wird.The invention relates to a burner system having at least two adjacent burners, each having at least one combustion chamber and a head end, the latter comprising at least one fuel injection and a fuel-air premix, each burner having 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 Hutoberseite and the head end thereby a burner plenum is formed.
  • In Verbrennungssystemen wie Gasturbinen, Flugtriebwerken, Raketenmotoren und Heizungsanlagen kann es zu thermoakustisch induzierten Verbrennungsschwingungen kommen. Diese entstehen durch eine Wechselwirkung der Verbrennungsflamme und der damit verbundenen Wärmefreisetzung mit akustischen Druckschwankungen. Durch eine akustische Anregung kann die Lage der Flamme, die Flammenfrontfläche oder die Gemischzusammensetzung schwanken, was wiederum zu Schwankungen der Wärmefreisetzung führt. Bei konstruktiver Phasenlage kann es zu einer positiven Rückkopplung und Verstärkung kommen. Eine so verstärkte Verbrennungsschwingung kann zu erheblichen Lärmbelastungen und Schädigungen durch Vibrationen führen.In combustion systems such as gas turbines, aircraft engines, rocket engines and heating systems, thermoacoustically induced combustion oscillations can occur. These arise through an interaction of the combustion flame and the associated heat release with acoustic pressure fluctuations. By means of an acoustic excitation, the position of the flame, the flame front surface or the mixture composition can fluctuate, which in turn leads to fluctuations of the heat release. With a constructive phase position, positive feedback and amplification can occur. Such an increased combustion vibration can lead to considerable noise and vibration damage.
  • Eine Lösung zur Dämpfung von Verbrennungsschwingungen ist in der EP 1703208 Eine Lösung zur Dämpfung von Verbrennungsschwingungen ist in der EP 1703208 offenbart. disclosed. Dieses Dokument beschreibt ein Brennersystem 1 mit mehreren benachbarten Brennern 8, von denen jeder ein Kopfende aufweist, wobei letzteres zwei Kraftstoffeinspritzungen 10, 12 sowie eine Kraftstoff-Luft Vormischung 13 umfasst, wobei jeder Brenner 8 einen Hut mit einer Hutseite und einer Hutoberseite aufweist, wobei die Hutoberseite in Strömungsrichtung gesehen vor dem Kopfende angeordnet ist, so dass zwischen der Hutoberseite und dem Kopfende ein Brenner-Plenum 7 ausgebildet wird, wobei das Brenner-Plenum mindestens eine akustische Wand 15 zwischen zwei Brennern 8 aufweist. This document describes a burner system 1 with several adjacent burners 8, each of which has a head end, the latter comprising two fuel injections 10, 12 and a fuel-air premix 13, each burner 8 having a hat with a hat side and a hat top, wherein the top of the hat is arranged in front of the head end, seen in the direction of flow, so that a burner plenum 7 is formed between the top of the hat and the head end, the burner plenum having at least one acoustic wall 15 between two burners 8. Weiterhin beschreibt D1, dass das Brennersystem auch mit mehreren rohrartigen Brennkammern (Flammrohren) 9 vorgesehen werden kann , so dass jeder Brenner eine Brennkammer 9 aufweist und die Wände 15 das Plenum 7 in mehreren Plenen unterteilen. Furthermore, D1 describes that the burner system can also be provided with several tubular combustion chambers (flame tubes) 9, so that each burner has a combustion chamber 9 and the walls 15 divide the plenum 7 into several plenums. A solution for damping combustion oscillations is in the A solution for damping combustion oscillations is in the EP 1703208 EP 1703208 disclosed. disclosed. This document describes a burner system 1 with a plurality of adjacent burners 8, each having a head end, the latter comprising two fuel injections 10, 12 and a fuel-air premix 13, each burner 8 having a hat-top and hat-top hat the top of the hat is arranged in front of the head end as seen in the flow direction, so that a burner plenum 7 is formed between the hat top and the head end, the burner plenum having at least one acoustic wall 15 between two burners 8. Furthermore, D1 describes that the burner system can also be provided with a plurality of tubular combustion chambers (flame tubes) 9, so that each burner has a combustion chamber 9 and the walls 15 divide the plenum 7 into several plenums. This document describes a burner system 1 with a plurality of adjacent burners 8, each having a head end, the latter comprising two fuel injections 10, 12 and a fuel-air premix 13, each burner 8 having a hat-top and hat-top hat the top of the hat is arranged in front of the head end as seen in the flow direction, so that a burner plenum 7 is formed between the hat top and the head end, the burner plenum having at least one acoustic wall 15 between two burners 8. Furthermore, D1 describes that the burner system can also be provided with a plurality of tubular combustion chambers (flame tubes) 9, so that each burner has a combustion chamber 9 and the walls 15 divide the plenum 7 into several plenums.
  • Wesentlich beeinflusst werden diese thermoakustisch hervorgerufenen Instabilitäten durch die akustischen Eigenschaften des Brennraumes und die am Brennraumeintritt und Brennraumaustritt sowie an den Brennkammerwänden vorliegenden Randbedingungen. Die akustischen Eigenschaften können durch den Einbau von Helmholtz-Resonatoren verändert werden. These 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. The acoustic properties can be changed by installing Helmholtz resonators.
  • Die WO 93/10401 A1 Die WO 93/10401 A1 zeigt eine Einrichtung zur Unterdrückung von Verbrennungsschwingungen in einer Brennkammer einer Gasturbinenanlage. shows a device for suppressing combustion vibrations in a combustion chamber of a gas turbine plant. Ein Helmholtz-Resonator ist mit einer Brennstoffzuführleitung strömungstechnisch verbunden. A Helmholtz resonator is fluidically connected to a fuel supply line. Die akustischen Eigenschaften der Zuführleitung bzw. des akustischen Gesamtsystems werden hierdurch so verändert, dass Verbrennungsschwingungen unterdrückt werden. The acoustic properties of the supply line or the overall acoustic system are thereby changed in such a way that combustion vibrations are suppressed. Es hat sich allerdings gezeigt, dass diese Maßnahme nicht in allen Betriebszuständen ausreicht, da es auch bei einer Unterdrückung von Schwingungen in der Brennstoffleitung zu Verbrennungsschwingungen kommen kann. It has been shown, however, that this measure is not sufficient in all operating states, since combustion vibrations can occur even when vibrations are suppressed in the fuel line. The The WO 93/10401 A1 WO 93/10401 A1 shows a device for suppressing combustion oscillations in a combustion chamber of a gas turbine plant. 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. 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. The acoustic properties of the supply line or the overall acoustic system are thereby changed so that combustion oscillations are suppressed. However, it has been 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. However, it has been 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.
  • Die WO 03/074936A1 Die WO 03/074936A1 zeigt eine Gasturbine, mit einem Brenner, der in eine Brennkammer mündet, wobei diese Mündung ringförmig von einem Helmholtz-Resonator umgeben ist. shows a gas turbine with a burner opening into a combustion chamber, this opening being surrounded in the shape of a ring by a Helmholtz resonator. Hierdurch werden Verbrennungsschwingungen durch engen Kontakt zur Flamme effektiv gedämpft, wobei gleichzeitig Temperaturungleichmäßigkeiten vermieden werden. This effectively dampens combustion oscillations through close contact with the flame, while at the same time avoiding temperature irregularities. In dem Helmholtz-Resonator sind Röhrchen angebracht, welche eine Frequenzanpassung bewirken. In the Helmholtz resonator, tubes are attached which effect a frequency adjustment. The The WO 03 / 074936A1 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. shows a gas turbine, with a burner which opens into a combustion chamber, said mouth is annularly surrounded by a Helmholtz resonator. As a result, combustion vibrations are effectively attenuated by close contact with the flame, while avoiding temperature nonuniformity. As a result, combustion vibrations are effectively attenuated by close contact with the flame, while avoiding temperature nonuniformity. In the Helmholtz resonator tubes are mounted, which cause a frequency adjustment. In the Helmholtz resonator tubes are mounted, which cause a frequency adjustment.
  • In der EP 0 597 138 A1 In der EP 0 597 138 A1 ist eine Gasturbinen-Brennkammer beschrieben, die im Bereich der Brenner luftgespülte Helmholtz-Resonatoren aufweist. describes a gas turbine combustion chamber which has air-purged Helmholtz resonators in the area of ​​the burners. Die Resonatoren sind alternierend an der Stirnseite der Brennkammer zwischen den Brennern angeordnet. The resonators are arranged alternately on the front side of the combustion chamber between the burners. Durch diese Resonatoren wird Schwingungsenergie von in der Brennkammer auftretenden Verbrennungsschwingungen absorbiert und die Verbrennungsschwingungen werden hierdurch gedämpft. Vibrational energy from combustion vibrations occurring in the combustion chamber is absorbed by these resonators and the combustion vibrations are thereby dampened. In the In the EP 0 597 138 A1 EP 0 597 138 A1 a gas turbine combustor is described which has air-purged Helmholtz resonators in the burner. A gas turbine combustor is described 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. 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. By these resonators, vibration energy is absorbed by combustion vibrations occurring in the combustion chamber and the combustion vibrations are thereby damped.
  • Jeder dieser Resonatoren weist funktionsbedingt eine verbindende Öffnung mit der Brennkammer auf, die durch eine bestimmte Luftmenge gesperrt werden muss. Diese Luftmenge steht, bei Anbringung der Resonatoren an der Brennkammerwand, anschließend nicht mehr für die Verbrennung zur Verfügung, da sie am Brenner vorbeigeführt wird. Damit werden die Flammentemperatur sowie die NOx-Emissionen erhöht.Each of these resonators has functionally a connecting opening with the combustion chamber, which must be blocked by a certain amount of air. This amount of air is, when attaching the resonators on the combustion chamber wall, then no longer available for combustion, as it is passed by the burner. This increases the flame temperature and NOx emissions.
  • Die Aufgabe der vorliegenden Erfindung ist daher die Angabe eines Brennersystems, welche zur Dämpfung von Verbrennungsschwingungen einsetzbar ist und welche die obige Problematik vermeidet.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.
  • Erfindungsgemäß ist ein Brennersystem mit zumindest zwei benachbarten Brennern vorgesehen, von denen jeder zumindest eine Brennkammer und ein Kopfende aufweist, wobei letzteres zumindest eine Kraftstoffeinspritzung sowie eine Kraftstoff-Luft Vormischung umfasst. Dabei weist jeder Brenner einen Hut mit einer Hutseite und einer Hutoberseite auf, wobei zumindest die Hutoberseite in Strömungsrichtung gesehen vor dem Kopfende angeordnet ist. Zwischen der Hutoberseite und dem Kopfende wird dadurch ein Brenner-Plenum ausgebildet.According to the invention, a burner system is provided with at least two adjacent burners, each of which has at least one combustion chamber and a head end, the latter comprising at least one fuel injection and a fuel-air premix. In this case, each 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 of a burner plenum is formed.
  • Es ist bekannt, dass die Leistung von Gasturbinen beim Einsatz von Rohrbrennkammern durch das Auftreten von thermoakustischen Schwingungen in diesen Brennkammern begrenzt wird. Erfindungsgemäß wurde nun erkannt, dass speziell bei den Rohrbrennkammern die akustische Interaktion zweier benachbarter Brennkammern wichtig ist. Hier stellen sich Moden ein, die sich über die Verbindung vor der Turbine von einer Brennkammer in die andere ausbreiten.It is known that the performance of gas turbines when using tube combustion chambers is limited by the occurrence of thermoacoustic oscillations in these combustion chambers. According to the invention, it has now been recognized that the acoustic interaction of two adjacent combustion chambers is particularly important in the tube combustion chambers. Here, modes are established that spread over the connection in front of the turbine from one combustion chamber to the other.
  • Die akustische Analyse der Verteilungen des akustischen Druckes zeigt, dass sich hierbei eine Modenform einstellt, bei der benachbarte Brennkammern einschließlich der Plenen stromauf der Brennkammern gegenphasig schwingen. Erfindungsgemäß weisen nun die zumindest zwei Brenner-Plenen eine akustische Verbindung auf.The acoustic analysis of the acoustic pressure distributions shows that this results in a mode shape in which adjacent combustion chambers, including the plenums, oscillate out of phase upstream of the combustion chambers. According to the invention, the at least two burner plenums now have an acoustic connection.
  • Durch diese eine geeignet ausgeführte akustische Verbindung benachbarter Brennkammern beziehungsweise ihrer Plenen, kann die Möglichkeit zur Ausbildung dieser Modenform unterdrückt und verhindert werden. Somit ist es möglich thermoakustische Schwingungen zu dämpfen oder gar weitestgehend zu verhindern.By means of this suitably designed acoustic connection of adjacent combustion chambers or their plenums, it is possible to form this mode shape be suppressed and prevented. Thus, it is possible to dampen thermoacoustic vibrations or even prevent as far as possible.
  • Erfindungsgemäß ist die Hutseite zumindest teilweise um das Kopfende herum angeordnet, so dass dabei die Hutseite in einer radialen Richtung vom Kopfende beabstandet ist.According to the invention, 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.
  • In bevorzugter Ausgestaltung ist durch die Hutseite und das Kopfende ein Kanal ausgebildet. Durch diesen Kanal wird Verdichterluft zu dem Plenum geleitet. Diese Verdichterluft kühlt somit die Außenseite der Brennkammer und vermindert so eine Überhitzung der Brennkammer. Idealerweise wird so die Verdichterluft vorgewärmt, so dass eine stabilere Verbrennung stattfinden kann.In a preferred embodiment, 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.
  • Erfindungsgemäß ist die akustische Verbindung ein Brenner-Plenen verbindendes Rohr, insbesondere ein ringfömig ausgebildetes Rohr oder ein Kanal. Diese Verbindung lässt sich besonders einfach konstruktiv umsetzten.According to the invention, the acoustic connection is a burner plenum connecting pipe, in particular a ringfömig trained pipe or a channel. This connection is particularly easy to implement constructively.
  • Bevorzugt weist jeder Brenner mit seinem Brenner-Plenum eine akustische Verbindung zu den jeweils benachbarten Brenner bzw. Brenner-Plenen auf. Somit lässt sich optimal die Ausbildung einer Modenform aller vorhanden Brenner unterdrücken. Each burner with its burner plenum preferably has an acoustic connection to the respectively adjacent burners or burner plenums. Thus, optimally suppress the formation of a mode shape of all available burner.
  • Vorteilhafterweise umfasst eine Gasturbine ein solches Brennersystem. Advantageously, a gas turbine comprises such a burner system.
  • Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren.
  • Fig. 1 Fig. 1
    zeigt schematisch eine Gasturbine in einem Längsteilschnitt, shows schematically a gas turbine in a partial longitudinal section,
    Fig. 2 Fig. 2
    zeigt eine Rohrbrennkammer mit Hut, shows a tube combustion chamber with a hat,
    Fig. 3 Fig. 3
    zeigt schematisch die erfindungsgemäße Verbindung zwischen den Brenner-Plenen. shows schematically the connection according to the invention between the burner plenums.
    Further features, properties and advantages of the present invention will become apparent from the following description of embodiments with reference to the accompanying figures. Further features, properties and advantages of the present invention will become apparent from the following description of with reference to the accompanying figures.
    Fig. 1 Fig. 1
    shows schematically a gas turbine in a longitudinal partial section, shows schematically a gas turbine in a longitudinal partial section,
    Fig. 2 Fig. 2
    shows a tube burning chamber with hat, shows a tube burning chamber with hat,
    Fig. 3 Fig. 3
    shows schematically the compound of the invention between the burner plenums. shows schematically the compound of the invention between the burner plenums.
  • Die Figur 1 Die Figur 1 zeigt beispielhaft eine Gasturbine 1 in einem Längsteilschnitt. shows an example of a gas turbine 1 in a partial longitudinal section. The The FIG. FIG. 1 1 shows by way of example a gas turbine 1 in a longitudinal partial section. shows by way of example a gas turbine 1 in a longitudinal partial section.
  • Die Gasturbine 1 weist im Inneren einen um eine Rotationsachse 2 drehgelagerten Rotor 3 mit einer Welle auf, der auch als Turbinenläufer bezeichnet wird. 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.
  • Entlang des Rotors 3 folgen aufeinander ein Ansauggehäuse 4, ein Verdichter 5, eine beispielsweise torusartige Brennkammer 6, insbesondere Rohr- oder Ringbrennkammer, mit mehreren koaxial angeordneten Brennern 7, eine Turbine 8 und das Abgasgehäuse 9.Along the rotor 3 follow one another a suction housing 4, a compressor 5, for example a toroidal combustion chamber 6, in particular pipe or annular combustion chamber, with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing. 9
  • Die Brennkammer 6 kommuniziert mit einem beispielsweise ringförmigen Heißgaskanal 11. Dort bilden beispielsweise vier hintereinander geschaltete Turbinenstufen 12 die Turbine 8. The combustion chamber 6 communicates with, for example, a ring-shaped hot gas channel 11. There, for example, four turbine stages 12 connected in series form the turbine 8.
  • Jede Turbinenstufe 12 ist beispielsweise aus zwei Schaufelringen gebildet. In Strömungsrichtung eines Arbeitsmediums 13 gesehen folgt im Heißgaskanal 11 einer Leitschaufelreihe 15 eine aus Laufschaufeln 20 gebildete Reihe 25. 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.
  • Während des Betriebes der Gasturbine 1 wird vom Verdichter 5 durch das Ansauggehäuse 4 Luft 35 angesaugt und verdichtet. Die am turbinenseitigen Ende des Verdichters 5 bereitgestellte verdichtete Luft wird zu den Brennern 7 geführt und dort mit einem Brennstoff vermischt. Das Gemisch wird dann unter Bildung des Arbeitsmediums 13 in der Brennkammer 6 verbrannt. Von dort aus strömt das Arbeitsmedium 13 entlang des Heißgaskanals 11 vorbei an den Leitschaufeln 30 und den Laufschaufeln 20. An den Laufschaufeln 20 entspannt sich das Arbeitsmedium 13 impulsübertragend, so dass die Laufschaufeln 20 den Rotor 3 antreiben und dieser die an ihn angekoppelte Arbeitsmaschine.During operation of the gas turbine 1 4 air 35 is sucked and compressed by the compressor 5 through the intake housing. The compressed air provided at the turbine-side end of the compressor 5 is led to the burners 7 where it is mixed with a fuel. The mixture is then burned to form the working medium 13 in the combustion chamber 6. From there, the working fluid 13 flows along the hot gas channel 11 past the guide vanes 30 and the blades 20. At the blades 20, the working fluid 13 relaxes impulsively, so that the blades 20 drive the rotor 3 and this the driven machine coupled to it.
  • Vorzugsweise wird der Brenner 7 in Verbindung mit einer sogenannten Rohrbrennkammer 6 (Fig. 2) verwendet. Hierbei weist die Gasturbine 1 mehrere, ringförmig angeordnete Rohrbrennkammern 6 auf, deren abströmseitigen Öffnungen in den ringförmigen Heißgaskanal 11 turbineneingansseitig münden. Dabei sind vorzugsweise an jeder dieser Rohrbrennkammer mehrere, beispielsweise sechs oder acht, Brenner 7 an dem gegenüberliegenden Ende der abströmseitigen Öffnung der Rohrbrennkammer 6 zumeist ringförmig um einen Pilotbrenner angeordnet.Preferably, the burner 7 in conjunction with a so-called tube combustion chamber 6 ( Fig. 2 ) used. ) used. Here, 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. Here, 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. In this case, preferably at each of these tube combustion chamber 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. In this case, preferably at each of these tube combustion chamber 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.
  • Figur 2 zeigt abschnittweise einen Rohrbrenner 7 schematisch. shows sections of a tube burner 7 schematically. Der Brenner 7 umfasst ein Kopfende 51, ein Überleitkanal (Transition) 52, und dazwischen einen Liner 53. Dabei wird als "Kopfende (Head-End) 51" im Wesentlichen der Teilabschnitt der Kraftstoffeinspritzung 55/Kraftstoff-Luft Vormischung 56 des Brenners bezeichnet. The burner 7 comprises a head end 51, a transfer channel (transition) 52, and a liner 53 between them. The “head end 51” essentially denotes the subsection of the fuel injection 55 / fuel-air premix 56 of the burner. Der Liner 53 erstreckt sich vom Kopfende zu dem Transition 52 auf beliebige Weise. The liner 53 extends from the head end to the transition 52 in any way. Durch Liner 53 und Strömungsmantel 60 wird eine Ringpassage 57 ausgebildet durch die Verbrennungs-/Kühlluft 65 eingeströmt. An annular passage 57 through which the combustion / cooling air 65 flows is formed by the liner 53 and the flow jacket 60. Der Raum vor der Kraftstoffeinspritzung 55 bzw. The space in front of the fuel injection 55 or FIG. FIG. 2 2 shows a section of a tube burner 7 schematically. 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 burner 7 comprises a head end 51, a transition 52 and a liner 53 therebetween. Here, the "head end 51" is essentially the subsection of the fuel injection 55 / fuel-air premix 56 of the burner. Here, 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. The liner 53 extends from the head end to the transition 52 in any manner. By liner 53 and flow jacket 60, an annular passage 57 is formed by the combustion / cooling air 65 flows. By liner 53 and flow jacket 60, an annular passage 57 is formed by the combustion / cooling air 65 flows. The space before the fuel injection 55 or The space before the fuel injection 55 or
  • Kraftstoff / Luftvormischung 56 wird als Brenner-Plenum (Plenum) 100 bezeichnet. Der Brenner 7 weist einen Hut 110 mit einer Hutseite 150 und einer Hutoberseite 170 auf. Dabei ist zumindest die Hutoberseite 170 in Strömungsrichtung gesehen vor dem Kopfende 51 angeordnet, wodurch zwischen der Hutoberseite 170 und dem Kopfende 51 ein Brenner-Plenum 100 ausgebildet wird. Der Hut 110 weist eine brennkammerzugewandte Seite 140 und eine brennkammerabgewandte Seite 120 auf (Fig. 3 ). ). Dabei ist der Hut 110 mit der Hutseite 150 quasi außerhalb der Maschine angeordnet. The hat 110 with the hat side 150 is arranged quasi outside the machine. 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. In this case, at least the hat top side 170 is arranged upstream of the head end 51, as seen in the flow direction, whereby a burner plenum 100 is formed between the hat top side 170 and the head end 51. The hat 110 has a combustion chamber-facing side 140 and a combustion chamber-facing side 120 (FIG. 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. In this case, at least the hat top side 170 is arranged upstream of the head end 51, as seen in the flow direction, whereby a burner plenum 100 is formed between the hat top side 170 and the head end 51. The hat 110 has a combustion chamber-facing side 140 and a combustion chamber-facing side 120 ( FIG. Fig. 3 Fig. 3 ). ). In this case, the hat 110 with the hat side 150 is arranged virtually outside the machine. In this case, the hat 110 with the hat side 150 is arranged virtually outside the machine.
  • Fig. 3 zeigt das erfindungsgemäße Brennersystem mit zwei benachbarten Brennern 7, von denen jeder eine Rohrbrennkammer 6 und ein Kopfende 51 aufweist. shows the burner system according to the invention with two adjacent burners 7, each of which has a tubular combustion chamber 6 and a head end 51. Jeder der Brenner 7 weist einen Hut 110 mit einer Hutseite 150 und einer Hutoberseite 170 auf. Each of the burners 7 has a hat 110 with a hat side 150 and a hat top 170. Dabei ist zumindest die Hutoberseite 170 in Strömungsrichtung gesehen vor dem Kopfende 51 angeordnet, wodurch zwischen der Hutoberseite 170 und dem Kopfende 51 ein Brenner-Plenum 100 ausgebildet wird. In this case, at least the top side 170 of the hat is arranged in front of the head end 51 as seen in the flow direction, as a result of which a burner plenum 100 is formed between the top side 170 and the head end 51. Zwischen den zwei benachbarten Brenner-Plenen 100 ist eine akustische Verbindung 130 vorhanden. There is an acoustic connection 130 between the two adjacent burner plenums 100. Diese akustische Verbindung ist hier vorteilhafterweise ringförmig und verbindet somit die jeweiligen benachbarten Brenner-Plenen 100 der Brenner 7 gesamten Gasturbine miteinander. This acoustic connection is advantageously ring-shaped here and thus connects the respective adjacent burner plenums 100 of the burner 7 of the entire gas turbine to one another. Die ringförmige Verbindung ist mittels eines Rohres realisiert, dass die einzelnen Plenen 100 miteinander verbindet. The ring-shaped connection is implemented by means of a tube that connects the individual plenums 100 to one another. Im Bereich der Plenen 100 ist eine solche Verbindung 130 ohne großen konstruktiven Aufwand realisierbar. In the area of ​​the plenums 100, such a connection 130 can be implemented without great structural effort. Die ringförmige Verbindung endet somit an dem Brenner-Plenum 100 an dem sie begonnen hat. The annular connection thus ends at the burner plenum 100 at which it began. Es stelle sich somit keine Moden mehr ein, die sich über die Verbindung vor der Turbine von einer Brennkammer in die andere ausbreiten, so dass die Brennkammern mit ihren Plenen gegenphasig schwingen. There are thus no more modes that propagate from one combustion chamber to the other via the connection in front of the turbine, so that the combustion chambers with their plenums oscillate in phase opposition. Die akustische Verbindung 130 unterdrückt und verhindert die Ausbildung einer solchen Modenform. The acoustic connection 130 suppresses and prevents the formation of such a mode shape. Fig. 3 Fig. 3 shows the burner system according to the invention with two adjacent burners 7, each of which has a tube combustion chamber 6 and a head end 51. Each of the burners 7 has a hat 110 with a hat side 150 and a hat top 170. In this case, at least the hat top side 170 is arranged upstream of the head end 51, as seen in the flow direction, whereby a burner plenum 100 is formed between the hat top side 170 and the head end 51. An acoustic connection 130 is present between the two adjacent burner plenums 100. This acoustic connection is here advantageously annular and thus connects the respective adjacent burner plenums 100 of the burner 7 the entire gas turbine with each other. shows the burner system according to the invention with two adjacent burners 7, each of which has a tube combustion chamber 6 and a head end 51. Each of the burners 7 has a hat 110 with a hat side 150 and a hat top 170. In This case, at least the hat top side 170 is arranged upstream of the head end 51, as seen in the flow direction, whereby a burner plenum 100 is formed between the hat top side 170 and the head end 51. An acoustic connection 130 is present between the two adjacent burner plenums 100. This acoustic connection is advantageously annular and thus connects the respective adjacent burner plenums 100 of the burner 7 the entire gas turbine with each other. The annular connection is realized by means of a tube that connects the individual planks 100 with each other. The annular connection is realized by means of a tube that connects the individual planks 100 with each other. In the area of plenums 100 such a connection 130 can be realized without great constructive effort. In the area of ​​plenums 100 such a connection 130 can be realized without great constructive effort. The annular connection thus ends at the burner plenum 100 at which it has begun. The annular connection thus ends at the burner plenum 100 at which it has begun. It no longer fades in modes that spread over the connection in front of the turbine from one combustion chamber to the other, so that the combustion chambers oscillate with their plumes in phase opposition. It no longer fades in modes that spread over the connection in front of the turbine from one combustion chamber to the other, so that the combustion chambers oscillate with their plumes in phase opposition. The acoustic connection 130 suppresses and prevents the formation of such a mode shape. The acoustic connection 130 suppresses and prevents the formation of such a mode shape.

Claims (6)

  1. Burner system having at least two adjacent burners (7) that are separate from each other, each of which has at least one combustion chamber (6) and a head end (51), wherein the latter comprises at least one fuel injection means (55) and a fuel-air premix means (56), wherein each burner (7) has a cap (110) having a cap side (150) and a cap top side (170), wherein at least the cap top side (170) is arranged ahead of the head end (51), viewed in the direction of flow, such that a burner plenum (100) is formed between the cap top side (170) and the head end (51),
    characterised in that the cap side (150) is arranged at least partially around the head end (51), in that the cap side (150) is spaced apart from the head end (51) in a radial direction (r), and in that the at least two burner plenums (100) have an acoustic connection (130) and the acoustic connection (130) is a tube connecting burner plenums (100).
  2. Burner system according to claim 1,
    characterised in that a channel (125) is formed by the cap side (150) and the head end (51).
  3. Burner system according to claim 1 or 2,
    characterised in that the acoustic connection (130) is annular.
  4. Burner system according to one of the preceding claims,
    characterised in that the acoustic connection (130) is a channel connecting burner plenums (100).
  5. Burner system according to one of the preceding claims,
    characterised in that each burner (7) with its burner plenum (100) has an acoustic connection (130) to the adjacent burner (7) or burner plenums (100) in each case.
  6. Gas turbine comprising a compressor, a turbine and a burner system according to one of the preceding claims.
EP20100161306 2010-04-28 2010-04-28 Combustion system for dampening such a combustion system Not-in-force EP2383515B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20100161306 EP2383515B1 (en) 2010-04-28 2010-04-28 Combustion system for dampening such a combustion system

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
EP20100161306 EP2383515B1 (en) 2010-04-28 2010-04-28 Combustion system for dampening such a combustion system
JP2013506557A JP5409959B2 (en) 2010-04-28 2011-03-07 Burner device and vibration damping method for this kind of burner
PCT/EP2011/053356 WO2011134706A1 (en) 2010-04-28 2011-03-07 Burner system and method for damping such a burner system
CN201180003126.9A CN102472495B (en) 2010-04-28 2011-03-07 Burner system and method for damping such a burner system
RU2012103903/06A RU2541478C2 (en) 2010-04-28 2011-03-07 Injector system and method of injector system damping
US13/388,347 US8631654B2 (en) 2010-04-28 2011-03-07 Burner system and method for damping such a burner system

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EP2383515A1 EP2383515A1 (en) 2011-11-02
EP2383515B1 true EP2383515B1 (en) 2013-06-19

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EP (1) EP2383515B1 (en)
JP (1) JP5409959B2 (en)
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WO (1) WO2011134706A1 (en)

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EP2474784A1 (en) * 2011-01-07 2012-07-11 Siemens Aktiengesellschaft Combustion system for a gas turbine comprising a resonator
US8684130B1 (en) * 2012-09-10 2014-04-01 Alstom Technology Ltd. Damping system for combustor
JP6075263B2 (en) * 2013-10-04 2017-02-08 株式会社デンソー Intake device for vehicle
CN106631905A (en) * 2016-12-29 2017-05-10 江苏华亘泰来生物科技有限公司 Processing method of 13C urea

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WO1993010401A1 (en) 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Arrangement for suppressing combustion-caused vibrations in the combustion chamber of a gas turbine system
EP0597138B1 (en) 1992-11-09 1997-07-16 Asea Brown Boveri AG Combustion chamber for gas turbine
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
DE19851636A1 (en) 1998-11-10 2000-05-11 Asea Brown Boveri Damping device for reducing vibration amplitude of acoustic waves for burner for internal combustion engine operation is preferably for driving gas turbo-group, with mixture area for air and fuel
RU2175743C2 (en) * 1999-02-10 2001-11-10 Государственное предприятие Научно-исследовательский институт машиностроения Method and device for gas-dynamic ignition
RU2200869C2 (en) * 2000-10-16 2003-03-20 Меринов Александр Генадьевич Fuel injection nozzle with prechamber
EP1342953A1 (en) 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Gas turbine
WO2004051063A1 (en) * 2002-12-02 2004-06-17 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, and gas turbine with the combustor
US6931833B2 (en) 2003-04-30 2005-08-23 United Technologies Corporation Pulse combustion device
JP4177727B2 (en) * 2003-07-31 2008-11-05 東京電力株式会社 Gas turbine combustor
DE602005001611T2 (en) * 2005-02-04 2008-03-13 Enel Produzione S.P.A. Damping of thermoacoustic oscillations in a gas turbine combustor with annular chamber
EP1762786A1 (en) 2005-09-13 2007-03-14 Siemens Aktiengesellschaft Process and apparatus to dampen thermo-accoustic vibrations, in particular within a gas turbine
JP4838763B2 (en) * 2007-06-11 2011-12-14 三菱重工業株式会社 Mounting structure of combustion vibration detector
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RU2387582C2 (en) * 2008-06-18 2010-04-27 Александр Сергеевич Артамонов Complex for reactive flight

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JP2013525737A (en) 2013-06-20
CN102472495B (en) 2014-07-09
WO2011134706A1 (en) 2011-11-03
JP5409959B2 (en) 2014-02-05
CN102472495A (en) 2012-05-23
RU2541478C2 (en) 2015-02-20
US20120291438A1 (en) 2012-11-22
US8631654B2 (en) 2014-01-21
RU2012103903A (en) 2013-08-10
EP2383515A1 (en) 2011-11-02

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