EP1114967B1 - Method and device for suppressing whirls in a combustion chamber of a turbo-engine - Google Patents
Method and device for suppressing whirls in a combustion chamber of a turbo-engine Download PDFInfo
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- EP1114967B1 EP1114967B1 EP01810007A EP01810007A EP1114967B1 EP 1114967 B1 EP1114967 B1 EP 1114967B1 EP 01810007 A EP01810007 A EP 01810007A EP 01810007 A EP01810007 A EP 01810007A EP 1114967 B1 EP1114967 B1 EP 1114967B1
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- burner
- combustion chamber
- mass flow
- flow
- shear layer
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2210/00—Noise abatement
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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
- 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 method according to the preamble of claim 4 and to a device according to the preamble of claim 1 for the suppression flow vortexes within a combustion chamber of a flow force engine.
- thermoacoustic oscillations which arise at the burner as fluid mechanical instability waves and lead to flow vortices. These strongly influence the entire combustion process and lead to undesirable periodic heat releases within the combustion chamber, which are associated with strong pressure fluctuations.
- the high pressure fluctuations are associated with high vibration amplitudes, which can lead to undesirable effects, such as a high mechanical load of the combustion chamber, increased NO x emissions by inhomogeneous combustion and even to extinguish the flame within the combustion chamber.
- Thermoacoustic oscillations are based at least in part on flow instabilities burner flow, which manifests itself in coherent flow structures, and which influence the mixing processes between air and fuel.
- cooling air In conventional Combustion chambers is cooling air in the manner of a cooling air film over the combustion chamber walls directed.
- the cooling air film In addition to the cooling effect, the cooling air film also has a sound-absorbing effect and contributes to the reduction of thermoacoustic vibrations.
- the cooling air flow significantly reduced in the combustion chamber and all the air is through the Burner passed is the sound-absorbing cooling air film is reduced, whereby the sound-absorbing effect is reduced and those with the unwanted Vibrations associated problems again occur increasingly.
- thermoacoustic vibration amplitudes involves the disadvantage that the injection of fuel at the head stage may be accompanied by an increase in NO x emission.
- thermoacoustic vibrations have shown that such unwanted coherent structures arise in mixing operations. Of particular importance here are those between two mixing Flow forming shear layers formed within the coherent structures become. Further details can be found in the following publications: Oster & Wygnanski 1982, "The forced mixing layer between parallel streams", Journal of Fluid Mechanics, Vol. 123, 91-130; Paschereit et al. 1995, “Experimental investigation of subharmonic resonance in an axisymmetric jet ", Journal of Fluid Mechanics, Vol. 283, 365-407).
- Document EP-A2-0 754 908 discloses a method and apparatus for suppression Flame / pressure fluctuations in a furnace. Usually, in such Firings pressure fluctuations occur due to the outer or peripheral areas the flame or the fuel / air flow rolling up ring vortices excited and amplified become. To prevent this ring vortex, it is proposed to use a flame Coat of gas to surround. This jacket has a higher flow velocity in the flame direction, as the peripheral area of the flame. This results in a boundary layer acceleration and the vortex formation can no longer occur.
- a gas turbine plant which is a special fuel lance having.
- the fuel lance which is located in a premix tube, comprises a cylindrical Lance body with a number of internal lines. Lead these internal lines via radial extensions for axial fuel injection and at the same time oblique injection openings at the top of the lance. This purge air is in a recirculation zone injected, which increases in size and so to improved flame stability leads.
- the invention is based on the object, a method for the suppression of thermoacoustic vibrations and Flow vortices within a combustion chamber of a turbomachine, in particular a gas turbine plant, to create, so that unwanted flow vortex, which form as coherent pressure fluctuation structures, efficient and extinguished without much additional energy.
- a turbomachine in particular a gas turbine plant
- the invention is based on the recognition that the place of origin of the coherent Structures the boundary or shear layer is directly at the burner outlet. Unlike the principle of anti-sound, in which an existing sound field through Insertion of a phase-shifted sound field of the same energy extinguished
- the invention is based on the direct influence of the shear layer itself, in which the thermoacoustic vibrations form. Due to the direct influence, in the form of a targeted injection of a mass flow, preferably a gaseous mass flow, such as air, nitrogen or natural gas, in the shear layer can, acting in the shear layer, the pressure fluctuations amplifying mechanisms are used to target the extinguish unwanted pressure fluctuations.
- thermoacoustic vibrations are extinguished.
- additional Energy sources as they are known from the anti-sound technology, are not required in the process according to the invention.
- the inventive method allows a direct excitation of the shear layer at the place of their formation, i. at the burner outlet.
- the burner has at least two hollow, in the flow direction of the Hot gases nested part body on whose center axes to each other offset, so that adjacent walls of the body part tangential Air inlet ducts for the inflow of combustion air into one of the partial bodies form predetermined interior, and wherein the burner at least one Has fuel nozzle.
- Such types of burners also known as cone burners, have at their burner outlet on a circular trained tear-off, on the burner side immediately adjacent an outlet channel is provided through the mass flow is injected into the, at the spoiler edge forming shear layer can be.
- the outlet channel is on the inside of the burner outlet provided directly at its trailing edge.
- the mass flow inflow is constant or preferably pulsed into the shear layer to be subsequently to mix with the hot gases.
- vibration damping is the pulsation frequency of the mass flow on the training behavior the undesirable one forming within the shear layer
- the unwanted flow vortex at a pulsation frequency between 1 Hz and 5 kHz, preferably between 50 Hz and 300 Hz, effectively suppressed become.
- thermoacoustic Vibrations characteristic signal is supplied, and in dependence of which generates an excitation signal through which in the boundary layer mass flow to be introduced is modulated. It is with known techniques possible for the training of thermoacoustic oscillations within the Boundary layer characteristic signal to capture, filter accordingly and phase-rotated and reinforces another control unit, which, in accordance with the above described closed loop works to supply.
- Fig. 1 is a schematic device shown for targeted suppression thermoacoustic oscillations within a combustion chamber 2.
- a cone burner 1 is shown with one in the flow direction immediately subsequent combustion chamber 2.
- the cone burner 1 has a circular design Burner outlet 3, which in particular formed as a sharp tear-off edge is.
- a mass flow preferably air, Nitrogen or natural gas can be applied specifically (see arrows).
- a liquid fuel can be used.
- a boundary or shear layer is formed 5 out, within the unwanted thermoacoustic vibrations arise.
- a controllable Valve 6 ensures that the mass flow is both continuous and also in the shear layer 5 can be fed.
- thermoacoustic vibrations it is possible to choose a fixed pulse rate, the in no fixed phase relation to those forming within the shear layer 5 thermoacoustic vibrations.
- the valve 6 under a closed loop specify a pulse rate that in a certain Relationship to the training behavior of the thermoacoustic vibrations within the shear layer 5 is. So can by suitable choice of a correct phase difference between the pulsation of the mass flow and a measured Excitation signal representing the thermoacoustic oscillations within the shear layer characterized, the coherence of the developing instability waves disturbed be, whereby the pulsation amplitudes are significantly reduced can.
- the excitation mechanism according to the invention In contrast to the acoustic stimulation using the anti-sounding technique are no high demands on the excitation mechanism according to the invention especially because of thermal conditions and functionality the damping mechanism is not significantly affected.
- the mode of action of the method according to the invention for the suppression of Flow vortices within combustion chambers of fluid engines is also from the diagram as shown in FIG. 2.
- To juxtapose an undamped Flow case (see the dashed line) compared to a damped Flow case (see solid line) is the diagram according to Fig. 2 serve that at a suppression of a pressure oscillation in the 100 Hz range has been recorded.
- the excitation of the mass flow is antisymmetric to the forming within the shear layer thermoacoustic Vibrations. Nitrogen was used as the mass flow.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Regulation And Control Of Combustion (AREA)
- Gas Burners (AREA)
Description
Die Erfindung bezieht sich auf ein Verfahren gemäss dem Oberbegriff des Anspruchs 4 sowie auf eine Vorrichtung gemäss dem Oberbegriff des Anspruchs 1 zur Unterdrückung von Strömungswirbeln innerhalb einer Brennkammer einer Strömungskraftmaschnine.The invention relates to a method according to the preamble of claim 4 and to a device according to the preamble of claim 1 for the suppression flow vortexes within a combustion chamber of a flow force engine.
Beim Betrieb von Strömungskraftmaschinen, wie beispielsweise Gasturbinenanlagen, treten in den Brennkammern häufig unerwünschte, so genannte thermoakustische Schwingungen auf, die am Brenner als strömungsmechanische Instabilitätswellen entstehen und zu Strömungswirbeln führen. Diese beeinflussen den gesamten Verbrennungsvorgang stark und führen zu unerwünschten periodischen Wärmefreisetzungen innerhalb der Brennkammer , die mit starken Druckschwankungen verbunden sind. Mit den hohen Druckschwankungen sind hohe Schwingungsamplituden verknüpft, die zu unerwünschten Effekten, wie etwa zu einer hohen mechanischen Belastung des Brennkammergehäuses, einer erhöhten NOx-Emission durch eine inhomogene Verbrennung und sogar zu einem Erlöschen der Flamme innerhalb der Brennkammer führen können.In the operation of turbomachines, such as gas turbine plants, often occur in the combustion chambers undesirable, so-called thermoacoustic oscillations, which arise at the burner as fluid mechanical instability waves and lead to flow vortices. These strongly influence the entire combustion process and lead to undesirable periodic heat releases within the combustion chamber, which are associated with strong pressure fluctuations. The high pressure fluctuations are associated with high vibration amplitudes, which can lead to undesirable effects, such as a high mechanical load of the combustion chamber, increased NO x emissions by inhomogeneous combustion and even to extinguish the flame within the combustion chamber.
Thermoakustische Schwingungen beruhen zumindest teilweise auf Strömungsinstabilitäten der Brennerströmung, die sich in kohärenten Strömungsstrukturen äußern, und die die Mischungsvorgänge zwischen Luft und Brennstoff beeinflussen. Bei herkömmlichen Brennkammern wird Kühlluft in Art eines Kühlluftfilm über die Brennkammerwände geleitet. Neben dem Kühleffekt wirkt der Kühlluftfilm auch schalldämpfend und trägt zur Verminderung von thermoakustischen Schwingungen bei. In modernen Gasturbinenbrennkammem mit hohen Wirkungsgraden, niedrigen Emissionen und einer konstanten Temperaturverteilung am Turbineneintritt ist der Kühlluftstrom in die Brennkammer deutlich reduziert und die gesamte Luft wird durch den Brenner geleitet. Jedoch reduziert sich zugleich auch der schalldämpfende Kühlluftfilm, wodurch die schalldämpfende Wirkung herabgesetzt wird und die mit den unerwünschten Schwingungen verbundenen Probleme wieder verstärkt auftreten.Thermoacoustic oscillations are based at least in part on flow instabilities burner flow, which manifests itself in coherent flow structures, and which influence the mixing processes between air and fuel. In conventional Combustion chambers is cooling air in the manner of a cooling air film over the combustion chamber walls directed. In addition to the cooling effect, the cooling air film also has a sound-absorbing effect and contributes to the reduction of thermoacoustic vibrations. In modern gas turbine combustors with high efficiencies, low emissions and a constant temperature distribution at the turbine inlet is the cooling air flow significantly reduced in the combustion chamber and all the air is through the Burner passed. However, at the same time the sound-absorbing cooling air film is reduced, whereby the sound-absorbing effect is reduced and those with the unwanted Vibrations associated problems again occur increasingly.
Eine weitere Möglichkeit der Schalldämpfung besteht im Ankoppeln so genannter Helmholtz-Dämpfern im Bereich der Brennkammer oder der Kühlluftzufuhr. Jedoch ist bei modernen Brennkammerkonstruktionen das Vorsehen derartiger Helmholtz-Dämpfer aufgrund enger Platzverhältnisse mit großen Schwierigkeiten verbunden.Another possibility of soundproofing is the coupling of so-called Helmholtz dampers in the area of the combustion chamber or the cooling air supply. however is the provision of such Helmholtz dampers in modern combustion chamber designs due to tight space conditions associated with great difficulties.
Daneben ist es bekannt dass den im Brenner auftretenden strömungsmechanischen Instabilitäten und den damit verbundenen Druckschwankungen dadurch entgegengetreten werden kann, indem die Flamme durch zusätzliche Eindüsung von Brennstoff stabilisiert werden kann. Eine derartige Eindüsung von zusätzlichem Brennstoff erfolgt über die Kopfstufe des Brenners, in der eine auf der Brennerachse liegende Düse für die Pilot-Brennstoffgaszuführung vorgesehen ist, sie führt zu einer Anfettung der zentralen Flammstabilisierungszone. Diese Methode der Verminderung von thermoakustischen Schwingungsamplituden ist jedoch mit dem Nachteil verbunden, dass die Eindüsung von Brennstoff an der Kopfstufe mit einer Erhöhung der NOx-Emission einhergehen kann.In addition, it is known that the fluid mechanical instabilities occurring in the burner and the associated pressure fluctuations can be counteracted by the flame being stabilized by additional injection of fuel. Such injection of additional fuel takes place via the head stage of the burner, in which a nozzle for the pilot fuel gas feed located on the burner axis is provided, which leads to an enrichment of the central flame stabilization zone. However, this method of reducing thermoacoustic vibration amplitudes involves the disadvantage that the injection of fuel at the head stage may be accompanied by an increase in NO x emission.
Nähere Untersuchungen zur Ausbildung thermoakustischer Schwingungen haben gezeigt, dass derartig unerwünschte kohärente Strukturen bei Mischvorgängen entstehen. Von besonderer Bedeutung sind hierbei die sich zwischen zwei mischenden Strömungen ausbildenden Scherschichten, innerhalb der kohärente Strukturen gebildet werden. Nähere Ausführungen hierzu sind folgenden Druckschriften zu entnehmen: Oster & Wygnanski 1982, "The forced mixing layer between parallel streams", Journal of Fluid mechanics, Vol. 123, 91-130; Paschereit et al. 1995, "Experimental investigation of subharmonic resonance in an axisymmetric jet", Journal of Fluid Mechanics, Vol. 283, 365-407).Further studies on the formation of thermoacoustic vibrations have have shown that such unwanted coherent structures arise in mixing operations. Of particular importance here are those between two mixing Flow forming shear layers formed within the coherent structures become. Further details can be found in the following publications: Oster & Wygnanski 1982, "The forced mixing layer between parallel streams", Journal of Fluid Mechanics, Vol. 123, 91-130; Paschereit et al. 1995, "Experimental investigation of subharmonic resonance in an axisymmetric jet ", Journal of Fluid Mechanics, Vol. 283, 365-407).
Wie aus den vorstehenden Artikeln hervorgeht, ist es möglich, die sich innerhalb der Scherschichten ausbildenden kohärenten Strukturen durch gezieltes Einbringen einer akustischen Anregung derart zu beeinflussen, dass Ihre Entstehung verhindert wird. Eine weitere Methode ist das Einbringen eines akustischen Gegenschallfeldes, so dass das vorhandene unerwünschte Schallfeld durch ein gezielt eingebrachtes, phasenverschobenes Schallfeld regelrecht ausgelöscht wird. Diese Antischall-Technik, benötigt jedoch verhältnismäßig viel Energie, die entweder extern dem Brennersystem zur Verfügung gestellt werden muss oder die dem gesamten System an einer anderen Stelle abzuzweigen ist. Dies führt jedoch zu einer, wenn auch geringen, aber dennoch vorhandenen Wirkungsgradeinbuße.As can be seen from the above articles, it is possible that within the Shear layers forming coherent structures by targeted introduction of a To influence acoustic stimulation in such a way that prevents their formation becomes. Another method is the introduction of an acoustic counter-field, so that the existing unwanted sound field by a deliberately introduced, phase-shifted sound field is virtually extinguished. This anti-noise technique, but requires a relatively large amount of energy, the either externally made available to the burner system or the to divert the whole system to another place. However, this leads to a, although low, but still existing loss of efficiency.
Die Schrift EP-A2-0 754 908 offenbart ein Verfahren und eine Vorrichtung zur Unterdrückung von Flammen-/Druckschwankungen bei einer Feuerung. Üblicherweise können bei solchen Feuerungen Druckschwankungen auftreten, die durch sich an den Aussen- bzw. Randbereichen der Flamme oder der Brennstoff/Luftströmung aufrollende Ringwirbel angeregt und verstärkt werden. Um diese Ringwirbel zu unterbinden, wird vorgeschlagen, die Flamme mit einem Mantel aus Gas zu umgeben. Dieser Mantel weist eine höhere Strömungsgeschwindigkeit in Flammenrichtung auf, als der Randbereich der Flamme. Hierdurch erfolgt eine Grenzschichtbeschleunigung und die Wirbelbildung kann nicht mehr auftreten.Document EP-A2-0 754 908 discloses a method and apparatus for suppression Flame / pressure fluctuations in a furnace. Usually, in such Firings pressure fluctuations occur due to the outer or peripheral areas the flame or the fuel / air flow rolling up ring vortices excited and amplified become. To prevent this ring vortex, it is proposed to use a flame Coat of gas to surround. This jacket has a higher flow velocity in the flame direction, as the peripheral area of the flame. This results in a boundary layer acceleration and the vortex formation can no longer occur.
Aus US-A-5,408,830 ist eine Gasturbinenanlage bekannt, die eine spezielle Brennstofflanze aufweist. Die Brennstofflanze, die sich in einem Vormischrohr befindet, umfasst einen zylindrischen Lanzenkörper mit einer Anzahl von internen Leitungen. Diesen intemen Leitungen führen über radiale Erweiterungen zur einer axialen Brennstoffeindüsung und gleichzeitig zu schrägen Eindüsungsöffnungen an der Spitze der Lanze. Diese Spülluft wird in eine Rezirkulationszone eingedüst, die sich vergrössert und so zu einer verbesserten Flammenstabilität führt.From US-A-5,408,830 a gas turbine plant is known, which is a special fuel lance having. The fuel lance, which is located in a premix tube, comprises a cylindrical Lance body with a number of internal lines. Lead these internal lines via radial extensions for axial fuel injection and at the same time oblique injection openings at the top of the lance. This purge air is in a recirculation zone injected, which increases in size and so to improved flame stability leads.
Der Erfindung liegt die Aufgabe zu Grunde, ein Verfahren zur Unterdrückung von thermoakustischen Schwingungen und Strömungswirbeln innerhalb einer Brennkammer einer Strömungskraftmaschine, insbesondere einer Gasturbinenanlage, zu schaffen, so dass unerwünschte Strömungswirbel, die sich als kohärente Druckschwankungsstrukturen ausbilden, effizient und ohne großen zusätzlichen Energieaufwand ausgelöscht werden. Die hierzu notwendigen Maßnahmen sollen einen geringen konstruktiven Aufwand verursachen und kostengünstig in ihrer Realisierung sein.The invention is based on the object, a method for the suppression of thermoacoustic vibrations and Flow vortices within a combustion chamber of a turbomachine, in particular a gas turbine plant, to create, so that unwanted flow vortex, which form as coherent pressure fluctuation structures, efficient and extinguished without much additional energy. The This necessary measures should cause a small design effort and be cost effective in their realization.
Die Lösung der der Erfindung zu Grunde liegenden Aufgabe ist in den Ansprüchen 1 und 14 angegeben. Den Erfindungsgedanken vorteilhaft weiterbildende Merkmale sind den Unteransprüchen zu entnehmen. The solution of the problem underlying the invention is in the claims 1 and 14 indicated. The concept of the invention advantageously further-forming features are the dependent claims refer to.
Erfindungsgemäß sieht das Verfahren gemäß dem Oberbegriff des Anspruchs 1 vor, den Massenstrom unmittelbar am Brenneraustritt an einer Abrisskante des Brenners in eine Scherschnicht einer bringen.According to the invention, the method according to the preamble of claim 1, the mass flow directly at the burner outlet at a spoiler lip of the burner in a Scherschnicht one bring.
Der Erfindung liegt die Erkenntnis zu Grunde, dass der Ort der Entstehung der kohärenten Strukturen die Grenz- bzw. Scherschicht unmittelbar am Brenneraustritt ist. Anders als das Prinzip des Antischalls, bei dem ein vorhandenes Schallfeld durch Einbringen eines phasenverschobenen Schallfeldes gleicher Energie ausgelöscht wird, basiert die Erfindung auf der unmittelbaren Beeinflussung der Scherschicht selbst, in der sich die thermoakustischen Schwingungen ausbilden. Durch die direkte Einflussnahme, in Form einer gezielten Injektion eines Massenstromes, vorzugsweise eines gasförmigen Massenstromes, wie Luft, Stickstoff oder Erdgas, in die Scherschicht können die, in der Scherschicht wirkenden, die Druckschwankungen verstärkenden Mechanismen genutzt werden, um gezielt die unerwünschten Druckschwankungen auszulöschen. So werden bereits kleinste, von außen in die Scherschicht eingrebrachte Störungen, in Form einer gezielten Injektion eines Massenstroms, verstärkt, wodurch die sich innerhalb der Scherschicht ausbildenden thermoakustischen Schwingungen ausgelöscht werden. Auf diese Weise ist man in der Lage, mit kleinen, extern induzierten Störsignalen die thermoakustischen Schwingungen gänzlich zu unterdrücken. Zusätzliche Energiequellen, wie sie von der Antischalltechnik her bekannt sind, sind beim erfindungsgemäßen Verfahren nicht erforderlich.The invention is based on the recognition that the place of origin of the coherent Structures the boundary or shear layer is directly at the burner outlet. Unlike the principle of anti-sound, in which an existing sound field through Insertion of a phase-shifted sound field of the same energy extinguished The invention is based on the direct influence of the shear layer itself, in which the thermoacoustic vibrations form. Due to the direct influence, in the form of a targeted injection of a mass flow, preferably a gaseous mass flow, such as air, nitrogen or natural gas, in the shear layer can, acting in the shear layer, the pressure fluctuations amplifying mechanisms are used to target the extinguish unwanted pressure fluctuations. Thus even the smallest interferences introduced from outside into the shear layer become, in the form of a targeted injection a mass flow, amplified, causing the inside of the shear layer forming thermoacoustic vibrations are extinguished. In this way one is able to deal with small, externally induced Interference signals to completely suppress the thermoacoustic vibrations. additional Energy sources, as they are known from the anti-sound technology, are not required in the process according to the invention.
Auf diese weise erlaubt das erfindungsgemäße Verfahren eine direkte Anregung der Scherschicht am Ort ihrer Entstehung, d.h. am Brenneraustritt.In this way, the inventive method allows a direct excitation of the shear layer at the place of their formation, i. at the burner outlet.
Typischerweise weist der Brenner mindestens zwei hohle, in Strömungsrichtung der Heißgase ineinander geschachtelte Teilkörper auf, deren Mittelachsen zueinander versetzt verlaufen, sodass benachbarte Wandungen der Teilkörper tangentiale Lufteintrittskanäle für die Einströmung von Verbrennungsluft in einen von den Teilkörpern vorgegebenen Innenraum bilden, und wobei der Brenner zumindest eine Brennstoffdüse aufweist. Derartige, auch als Kegelbrenner bezeichnete Brennertypen, weisen an ihrem Brenneraustritt eine kreisrund ausgebildete Abrisskante auf, an der Brennerseitig unmittelbar angrenzend ein Austrittskanal vorgesehen ist, durch den der Massenstrom in die, sich an der Abrisskante ausbildende Scherschicht injiziert werden kann. Vorzugsweise ist der Austrittskanal an der Innenseite des Brenneraustritts unmittelbar an seiner Abrisskante vorgesehen.Typically, the burner has at least two hollow, in the flow direction of the Hot gases nested part body on whose center axes to each other offset, so that adjacent walls of the body part tangential Air inlet ducts for the inflow of combustion air into one of the partial bodies form predetermined interior, and wherein the burner at least one Has fuel nozzle. Such types of burners, also known as cone burners, have at their burner outlet on a circular trained tear-off, on the burner side immediately adjacent an outlet channel is provided through the mass flow is injected into the, at the spoiler edge forming shear layer can be. Preferably, the outlet channel is on the inside of the burner outlet provided directly at its trailing edge.
Neben der Verwendung eines gasförmigen Massenstromes, wie vorstehend aufgezeigt, ist es auch möglich, einen flüssigen Massenstrom den Heißgasen beizumischen, beispielsweise in Form flüssigen Brennstoffs.In addition to the use of a gaseous mass flow, as indicated above, it is also possible to mix a liquid mass flow with the hot gases, for example in the form of liquid fuel.
Um gezielt die sich innerhalb der Scherschicht am Brenneraustritt ausbildenden thermoakustischen Schwingungen zu unterdrücken, ist der Massenstromzufluss konstant oder vorzugsweise gepulst in die Scherschicht einzubringen, um sich nachfolgend mit den Heißgasen zu vermischen. Für optimale Ergebnisse in der Schwingungsdämpfung ist die Pulsationsfrequenz des Massenstromes auf das Ausbildungsverhalten der sich innerhalb der Scherschicht ausbildenden, unerwünschten Strömungswirbel bzw. thermoakustischen Schwingungen abzustimmen. Erfahrungswerte zeigen, dass die unerwünschten Strömungswirbel bei einer Pulsationsfrequenz zwischen 1 Hz und 5 kHz, vorzugsweise zwischen 50 Hz und 300 Hz, effektiv unterdrückt werden.To specifically form within the shear layer at Brenner exit suppressing thermoacoustic oscillations, the mass flow inflow is constant or preferably pulsed into the shear layer to be subsequently to mix with the hot gases. For optimum results in vibration damping is the pulsation frequency of the mass flow on the training behavior the undesirable one forming within the shear layer To tune flow vortex or thermoacoustic oscillations. experience show that the unwanted flow vortex at a pulsation frequency between 1 Hz and 5 kHz, preferably between 50 Hz and 300 Hz, effectively suppressed become.
Von besonderem Vorteil ist es, wenn die Massenstromeinspeisung als Antwortsignal auf die sich innerhalb der Scherschicht ausbildenden thermoakustischen Schwingungen erfolgt. Dies setzt voraus, dass das Ausbildungsverhalten der Strömungswirbel innerhalb der Scherschicht erfasst wird und dass in Abhängigkeit davon ein entsprechendes Antwort- bzw. Anregungssignal generiert wird. Dies erfolgt vorzugsweise innerhalb eines geschlossenen Regelkreises, dem ein für die Ausbildung thermoakustischer Schwingungen charakteristisches Signal zugeführt wird, und der in Abhängigkeit davon ein Anregungssignal generiert, durch das der in die Grenzschicht einzubringende Massenstrom moduliert wird. Mit an sich bekannten Techniken ist es möglich, das für die Ausbildung von thermoakustischen Schwingungen innerhalb der Grenzschicht charakteristische Signal zu erfassen, entsprechend zu filtern und phasengedreht und verstärkt einer weiteren Regeleinheit, die nach Maßgabe des vorstehend geschilderten geschlossenen Regelkreises arbeitet, zuzuführen.It is particularly advantageous if the mass current feed in as a response signal to the forming within the shear layer thermoacoustic vibrations he follows. This assumes that the training behavior of the flow vortex is detected within the shear layer and that depending on a corresponding Response or excitation signal is generated. This is preferably done within a closed loop, the one for the formation of thermoacoustic Vibrations characteristic signal is supplied, and in dependence of which generates an excitation signal through which in the boundary layer mass flow to be introduced is modulated. It is with known techniques possible for the training of thermoacoustic oscillations within the Boundary layer characteristic signal to capture, filter accordingly and phase-rotated and reinforces another control unit, which, in accordance with the above described closed loop works to supply.
Demgegenüber kann aus Gründen geringen Aufwandes das die Massenstromeinspeisung bestimmende Anregungssignal auch von einer Steuereinheit geliefert werden, das in keiner bestimmten Phasenbeziehung zu den sich innerhalb der Scherschicht ausbildenden thermoakustischen Schwingungen steht. Dennoch kann auf diese Weise eine höchst effiziente Schwingungsunterdrückung erzielt werden.In contrast, for reasons of little effort that the mass flow feed determining excitation signal are also supplied by a control unit, that in no particular phase relationship to those within the shear layer forming thermoacoustic vibrations. Still, you can This way a highly efficient vibration suppression can be achieved.
Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnung exemplarisch. Es zeigen:
- Fig. 1
- schematische Darstellung der erfindungsgemäß ausgebildeten Anregungsvorrichtung, sowie
- Fig. 2
- Diagrammdarstellung zur Unterdrückungseffizienz mit Hilfe eines geschlossenen Regelkreises.
- Fig. 1
- schematic representation of the inventively designed excitation device, as well
- Fig. 2
- Diagram depiction of the suppression efficiency by means of a closed loop.
In Fig. 1 ist eine schematisierte Vorrichtung dargestellt zur gezielten Unterdrückung
thermoakustischer Schwingungen innerhalb einer Brennkammer 2. Stark schematisiert
ist ein Kegelbrenner 1 dargestellt, mit einer in Strömungsrichtung unmittelbar
anschließenden Brennkammer 2. Der Kegelbrenner 1 weist einen kreisförmig ausgebildeten
Brenneraustritt 3 auf, der insbesondere als scharfe Abrisskante ausgebildet
ist. An der Innenseite des Brenneraustritts 2 mündet, die Abrisskante zirkular umlaufend,
ein Austrittskanal 4, durch den ein Massenstrom, vorzugsweise Luft,
Stickstoff oder Erdgas gezielt ausgebracht werden kann (siehe Pfeile). Auch ein flüssiger Brennstoff kann verwendet werden. Unmittelbar in Strömungsrichtung
am Brenneraustritt 3 anschließend, bildet sich eine Grenz- bzw. Scherschicht
5 aus, innerhalb der die unerwünschten thermoakustischen Schwingungen
entstehen. Um diese effizient zu unterdrücken, erfolgt durch den Austrittskanal 4 eine
Eindüsung eines Massenstroms in die Scherschicht 5, innerhalb der Strömungswirbel
verstärkende Mechanismen wirken. Infolge dessen verstärken sich auch die durch den Massenstrom
in die Scherschichts induzierten Störungen entsprechend. Ein ansteuerbares
Ventil 6 sorgt dafür, dass der Massenstrom sowohl kontinuierlich als
auch in die Scherschicht 5 eingespeist werden kann.In Fig. 1 is a schematic device shown for targeted suppression
thermoacoustic oscillations within a
Grundsätzlich ist es möglich, eine fest vorgegebene Pulsfrequenz zu wählen, die in
keinem festen Phasenbezug zu den sich innerhalb der Scherschicht 5 ausbildenden
thermoakustischen Schwingungen steht. Jedoch kann das Ventil 6 im Rahmen eines
geschlossenen Regelkreises eine Pulsfrequenz vorgeben, die in einem bestimmten
Verhältnis zum Ausbildungsverhalten der thermoakustischen Schwingungen innerhalb
der Scherschicht 5 steht. So kann durch geeignete Wahl einer korrekten Phasendifferenz
zwischen der Pulsation des Massenstromes sowie eines gemessenen
Anregungssignals, das die thermoakustischen Schwingungen innerhalb der Scherschicht
charakterisiert, die Kohärenz der sich entwickelnden Instabilitätswellen gestört
werden, wodurch die Pulsationsamplituden entscheidend verringert werden
können. Im Gegensatz zur akustischen Anregung unter Verwendung der Antischalltechnik
sind an dem erfindungsgemäßen Anregungsmechanismus keine hohen Anforderungen
zu stellen, zumal auch thermische Rahmenbedingungen die Funktionalität
des Dämpfungsmechanismus nicht wesentlich beeinträchtigt.Basically, it is possible to choose a fixed pulse rate, the in
no fixed phase relation to those forming within the
Die Wirkungsweise des erfindungsgemäßen Verfahrens zur Unterdrückung von Strömungswirbeln innerhalb von Brennkammern von Strömungskraftmaschinen ist auch aus dem Diagramm gemäß Fig. 2 zu entnehmen. Zur Gegenüberstellung eines nichtgedämpften Strömungsfalls (siehe hierzu die gestrichelte Linie) gegenüber eines gedämpften Strömungsfalles (siehe hierzu durchgezogenen Linienzug) soll das Diagramm gemäß Fig. 2 dienen, das bei einer Unterdrückung einer Druckschwingung im 100 Hz-Bereich aufgenommen worden ist. Die Anregung des Massenstromes erfolgt antisymmetrisch zu den sich innerhalb der Scherschicht ausbildenden thermoakustischen Schwingungen. Als Massenstrom wurde Stickstoff verwandt. The mode of action of the method according to the invention for the suppression of Flow vortices within combustion chambers of fluid engines is also from the diagram as shown in FIG. 2. To juxtapose an undamped Flow case (see the dashed line) compared to a damped Flow case (see solid line) is the diagram according to Fig. 2 serve that at a suppression of a pressure oscillation in the 100 Hz range has been recorded. The excitation of the mass flow is antisymmetric to the forming within the shear layer thermoacoustic Vibrations. Nitrogen was used as the mass flow.
- 11
- Brennerburner
- 22
- Brennkammercombustion chamber
- 33
- Brenneraustrittburner outlet
- 44
- Austrittskanaloutlet channel
- 55
- Scherschichtshear layer
- 66
- VentilValve
Claims (19)
- Method of suppressing thermoacoustic vibrations and flow eddies within a combustion chamber (2) of a turbomachine, whereincharacterized in thata fuel/air mixture is provided in a burner (1) and is introduced into the combustion chamber (2) andthe fuel/air mixture inside the combustion chamber (2) is caused to ignite and hot gases are formed,the combustion chamber (2) being supplied with an additional mass flow,the mass flow is introduced directly at the burner outlet (3) into a shear layer (5) forming at a separation edge of the burner (1).
- Method according to Claim 1, characterized in that the fuel/air mixture is generated in a burner (1), which consists of at least two hollow partial bodies nested one within the other in the flow direction of the fuel/air mixture, the centre lines of which partial bodies are offset relative to one another in such a way that adjacent walls of the partial bodies form tangential air inlet ducts for the flow of combustion air into an internal space specified by the partial bodies, the burner (1) having at least one fuel nozzle.
- Method according to Claim 1 or 2, characterized in that the mass flow is introduced into the shear layer(s) on the inside of the burner outlet (3).
- Method according to one of Claims 1 to 3, characterized in that a gaseous mass flow of air, nitrogen or natural gas is introduced into the shear layer (s).
- Method according to one of Claims 1 to 3, characterized in that a liquid fuel is introduced as the mass flow into the shear layer (5).
- Method according to Claims 1 to 5, characterized in that the mass flow is intoduced continuously into the shear layer(s).
- Method according to one of Claims 1 to 5, characterized in that the mass flow is intoduced in pulse fashion into the shear layer(s).
- Method according to Claim 7, characterized in that the pulsed mixing of the mass flow takes place by means of a control unit (6).
- Method according to Claim 8, characterized in that the control unit (6) is operated with an open-chain or a closed-loop control circuit.
- Method according to one of Claims 7 to 9, characterized in that the mass flow is introduced into the shear layer(s) with a pulsation frequency between 1 Hz and 5 kHz, preferably with a frequency between 50 Hz and 300 Hz.
- Method according to Claim 10, characterized in that an open-chain control circuit generates an excitation signal which has no specified phase relationship to a measured signal which characterizes the thermoacoustic vibrations and flow eddies occurring within the combustion chamber (2).
- Method according to Claim 10, characterized in that a signal is supplied to a closed-loop control circuit which characterizes the thermoacoustic vibrations and flow eddies occurring in the combustion chamber (2), and which is used as the excitation signal for the pulsed mass flow.
- Method according to Claim 12, characterized in that the signal supplied to the closed-loop control circuit is measured, filtered, phase-shifted and amplified.
- Appliance for suppressing thermoacoustic vibrations and flow eddies within a combustion chamber (2) of a turbomachine, which comprisescharacterized in thata burner (1),a combustion chamber (2) arranged following the burner (1) andat least one outlet duct (4) for introducing an additional mass flow, which outlet duct (4) discharges into the combustion chamber (2),the at least one outlet duct (4) discharges into the combustion chamber (2) at the burner outlet (3) at a separation edge of the burner (1).
- Appliance according to Claim 14, characterized in that the at least one outlet duct (4) discharges into the combustion chamber (2) on the inner side of the burner outlet (3).
- Appliance according to Claim 14 or 15, characterized in that the burner (1) is a conical burner whose burner outlet (3) has a substantially circular contour along which, at least in part, the outlet duct (4) discharges.
- Appliance according to one of Claims 14 to 16, characterized in that a control unit, by means of which the mass flow can be introduced into the combustion chamber (2) in pulses, is provided in the feed region of the outlet duct (4).
- Appliance according to Claim 17, characterized in that the control unit is a valve (6).
- Appliance according to one of Claims 14 to 18, characterized in that the turbomachine is a gas turbine installation.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10000415A DE10000415A1 (en) | 2000-01-07 | 2000-01-07 | Method and device for suppressing flow vortices within a fluid power machine |
| DE10000415 | 2000-01-07 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1114967A1 EP1114967A1 (en) | 2001-07-11 |
| EP1114967B1 true EP1114967B1 (en) | 2005-11-16 |
Family
ID=7626921
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01810007A Expired - Lifetime EP1114967B1 (en) | 2000-01-07 | 2001-01-04 | Method and device for suppressing whirls in a combustion chamber of a turbo-engine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US6698209B1 (en) |
| EP (1) | EP1114967B1 (en) |
| JP (1) | JP4898004B2 (en) |
| DE (2) | DE10000415A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9759424B2 (en) * | 2008-10-29 | 2017-09-12 | United Technologies Corporation | Systems and methods involving reduced thermo-acoustic coupling of gas turbine engine augmentors |
| US10036266B2 (en) | 2012-01-17 | 2018-07-31 | United Technologies Corporation | Method and apparatus for turbo-machine noise suppression |
| US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
| US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
Family Cites Families (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6016866A (en) * | 1983-07-06 | 1985-01-28 | 品川白煉瓦株式会社 | Graphite-containing refractories |
| GB8329218D0 (en) * | 1983-11-02 | 1983-12-07 | Ffowcs Williams J E | Reheat combustion system for gas turbine engine |
| US4770626A (en) * | 1986-03-06 | 1988-09-13 | Sonotech, Inc. | Tunable pulse combustor |
| JPS62294815A (en) * | 1986-06-13 | 1987-12-22 | Toshiba Corp | Gas turbine combustor |
| JPH0772616B2 (en) * | 1989-05-24 | 1995-08-02 | 株式会社日立製作所 | Combustor and operating method thereof |
| CH680084A5 (en) * | 1989-06-06 | 1992-06-15 | Asea Brown Boveri | |
| CH680467A5 (en) * | 1989-12-22 | 1992-08-31 | Asea Brown Boveri | |
| JPH04203710A (en) * | 1990-11-30 | 1992-07-24 | Hitachi Ltd | Combustor of gas turbine |
| JP3197103B2 (en) * | 1993-03-08 | 2001-08-13 | 三菱重工業株式会社 | Premixed air combustion method |
| JP3435833B2 (en) * | 1993-09-17 | 2003-08-11 | 株式会社日立製作所 | Combustor |
| DE4339094A1 (en) * | 1993-11-16 | 1995-05-18 | Abb Management Ag | Damping of thermal-acoustic vibrations resulting from combustion of fuel |
| US5408830A (en) * | 1994-02-10 | 1995-04-25 | General Electric Company | Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines |
| JPH08278028A (en) * | 1995-04-06 | 1996-10-22 | Hitachi Ltd | Gas turbine combustor |
| ATE170968T1 (en) * | 1995-07-20 | 1998-09-15 | Dvgw Ev | METHOD AND DEVICE FOR SUPPRESSING FLAME/PRESSURE VIBRATIONS DURING A FIRING |
| DE19542918A1 (en) * | 1995-11-17 | 1997-05-22 | Asea Brown Boveri | Device for damping thermoacoustic pressure vibrations |
| EP0789193B1 (en) * | 1996-02-07 | 2002-04-10 | DVGW Deutscher Verein des Gas- und Wasserfaches -Technisch-wissenschaftliche Vereinigung- | Method and apparatus for suppressing flame and pressure vibrations in a furnace |
| JPH09236261A (en) * | 1996-02-28 | 1997-09-09 | Hitachi Ltd | Gas turbine combustor |
| DE19636093B4 (en) * | 1996-09-05 | 2004-07-29 | Siemens Ag | Method and device for acoustic modulation of a flame generated by a hybrid burner |
| DE19704540C1 (en) * | 1997-02-06 | 1998-07-23 | Siemens Ag | Method for actively damping a combustion oscillation and combustion device |
| JPH10300088A (en) * | 1997-04-23 | 1998-11-13 | Hitachi Ltd | Flame holding structure of combustor |
| EP0931979A1 (en) * | 1998-01-23 | 1999-07-28 | DVGW Deutscher Verein des Gas- und Wasserfaches -Technisch-wissenschaftliche Vereinigung- | Method and apparatus for supressing flame and pressure fluctuations in a furnace |
| EP0987495B1 (en) * | 1998-09-16 | 2003-10-29 | ALSTOM (Switzerland) Ltd | Method for minimizing thermo-acoustic vibrations in gas turbine combustion chambers |
| EP0987491B1 (en) * | 1998-09-16 | 2005-07-20 | ALSTOM Technology Ltd | Method for preventing flow instabilities in a burner |
| DE59811961D1 (en) * | 1998-11-09 | 2004-10-21 | Alstom Technology Ltd Baden | burner |
| DE19855034A1 (en) * | 1998-11-28 | 2000-05-31 | Abb Patent Gmbh | Method for charging burner for gas turbines with pilot gas involves supplying pilot gas at end of burner cone in two different flow directions through pilot gas pipes set outside of burner wall |
-
2000
- 2000-01-07 DE DE10000415A patent/DE10000415A1/en not_active Withdrawn
-
2001
- 2001-01-04 DE DE50108042T patent/DE50108042D1/en not_active Expired - Lifetime
- 2001-01-04 EP EP01810007A patent/EP1114967B1/en not_active Expired - Lifetime
- 2001-01-05 US US09/754,186 patent/US6698209B1/en not_active Expired - Lifetime
- 2001-01-09 JP JP2001001655A patent/JP4898004B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| EP1114967A1 (en) | 2001-07-11 |
| US6698209B1 (en) | 2004-03-02 |
| DE50108042D1 (en) | 2005-12-22 |
| DE10000415A1 (en) | 2001-09-06 |
| JP2001248833A (en) | 2001-09-14 |
| JP4898004B2 (en) | 2012-03-14 |
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