EP2233836A1 - Swirler, method for reducing flashback in a burner with at least one swirler and burner - Google Patents
Swirler, method for reducing flashback in a burner with at least one swirler and burner Download PDFInfo
- Publication number
- EP2233836A1 EP2233836A1 EP09155904A EP09155904A EP2233836A1 EP 2233836 A1 EP2233836 A1 EP 2233836A1 EP 09155904 A EP09155904 A EP 09155904A EP 09155904 A EP09155904 A EP 09155904A EP 2233836 A1 EP2233836 A1 EP 2233836A1
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- EP
- European Patent Office
- Prior art keywords
- swirl
- combustion air
- fuel
- flow
- channel
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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.)
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Classifications
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
- F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
Definitions
- the present invention relates to a swirl generator with a central fuel distributor element and to a burner with at least one swirl generator.
- the invention relates to a method for avoiding flashback in a burner comprising at least one swirl generator with a central fuel distributor element.
- Gas turbine burners with a central fuel distributor elements and the swirl generators surrounding the fuel distributor elements are, for example, in DE 10 2007 004 394 A1 , in US 2004/0055306 A1 and in US 6,082,111 described.
- the swirl generator extends from the central fuel distributor element to a surrounding the central fuel distributor element, an axial flow channel for combustion air limiting wall.
- the burners each comprise a plurality of such arrangements. In such burners, the profiles of the fuel injected into the flow channel are designed such that only very little fuel is supplied to the zone around the central fuel distributor element, so that only a very lean mixture forms in this zone. The reason for this is that a flashback should be avoided.
- a further object of the present invention is to provide an advantageous method for avoiding flashback in a burner with at least one swirl generator.
- a swirl generator comprises a central fuel distributor element, an outer wall surrounding the central fuel distributor element and defining an axial flow channel for combustion air, swirl vanes extending radially to the outer wall and imparting a tangential flow component to the flowing combustion air, and radially surrounding the central fuel distributor element inside the outer wall partition.
- the partition separates the flow channel into a radially inner channel section and a radially outer channel section.
- the partition in the axial direction of the swirl generator at least over the axial length of the swirl blades, but in particular also extend beyond the axial length.
- the radially inner channel section allows the combustion air to pass through without imparting a tangential flow component or by impinging on one of the orientation of the tangential flow component in the radially outer channel section opposite tangential flow component.
- the fuel lines for the swirl vanes located in the radially outer channel section can pass through the swirl vanes extend in the radially inner channel portion, for example. In the form of holes through the swirl blades.
- fuel outlet openings in the fuel piping or the swirl blades in the inner channel section are fuel outlet openings in the fuel piping or the swirl blades in the inner channel section. These can in particular be arranged so that they inject the fuel substantially perpendicular to the flow direction of the combustion air in the radially inner channel section in the combustion air.
- fuel outlet openings may be present, which may be arranged in particular so that they inject the fuel substantially perpendicular to the flow direction of the combustion air in the radially outer channel section into the combustion air.
- a uniform fuel profile can also be achieved in the radially outer channel section.
- the injection direction does not necessarily have to be perpendicular to the flow direction of the combustion air.
- the injection direction can basically be chosen freely.
- the fuel can also be perpendicular to the radial direction and / or opposite to the flow direction of the air flowing through the flow channel Combustion air and / or are supplied parallel to the flow direction of the flowing through the flow channel combustion air.
- Other, not expressly named directions and combinations are also possible. This applies both to the fuel supply in the inner channel section and to the fuel supply in the outer in the outer channel section.
- the dividing wall may at least partially have a conical shape, wherein the opening cross section of the radially inner channel section decreases in the direction of flow of the combustion air.
- the dividing wall projects beyond the outflow-side end of the outer wall. This development can be realized both in a conical partition, as well as in a non-conical partition.
- An inventive burner is equipped with at least one swirl generator according to the invention.
- the advantages described with respect to the swirl generator can be realized in a burner, which in particular can be a gas turbine burner.
- a method of preventing flashback in a burner comprising at least one swirl generator with a central fuel distributor element and an outer wall surrounding the central fuel distribution element and defining a combustion air axial flow channel.
- the combustion air flowing through the flow channel is imparted a tangential flow component in a radially outer channel region.
- the combustion air flowing through the flow channel does not impart a tangential flow component or a tangential flow component opposite the tangential flow component in the radially outer channel region.
- a particularly uniform fuel profile can be generated when fuel is supplied to the combustion air flowing through the flow channel.
- the fuel can in this case in particular be admixed perpendicular to the flow direction of the combustion air flowing through the flow channel and / or perpendicular to the radial direction.
- An admixing substantially opposite to the flow direction of the combustion air flowing through the flow channel and / or parallel to the flow direction of the combustion air flowing through the flow channel is possible alternatively or in addition to the aforementioned variants.
- FIG. 1 showing a highly schematic sectional view of a gas turbine, explaining the structure and function of a gas turbine.
- the gas turbine 1 comprises a compressor section 3, a combustion section 4, which in the present embodiment comprises a plurality of tube combustion chambers 5 with burners 6 arranged thereon, but in principle may also comprise an annular combustion chamber, and a turbine section 7.
- a rotor 9, also called a runner, extends extending through all sections and carries in the compressor section 3 compressor blade rings 11 and the turbine section 7 turbine blade rings 13.
- FIG. 2 shows a burner 6 of the combustion section 4 in a perspective view.
- the burner 6 comprises a fuel distributor 27, eight fuel nozzles 29 extending from the fuel distributor 27 and eight swirl generators 31 arranged in the region of the tips of the fuel nozzles 29.
- the fuel distributor 27 and the fuel nozzles 29 together form a burner housing through which fuel lines extend Extend injection openings, which are arranged within the swirl generator 31 and therefore in FIG. 2 are not recognizable.
- the burner can be connected to fuel supply lines.
- a flange 35 the burner 6 can be attached to a tube combustion chamber so that the fuel nozzles 29 point towards the interior of the combustion chamber.
- burner 6 has eight fuel nozzles 29, it is also possible to equip it with a different number of fuel nozzles 29.
- the number of fuel nozzles can be greater than or less than eight, for example, six fuel nozzles or twelve fuel nozzles may be present, each having its own swirl generator.
- a pilot fuel nozzle is usually arranged in the center of the burner. The pilot fuel nozzle is in for clarity FIG. 2 not shown.
- air from the compressor is passed through the swirl generators 31 where it is mixed with fuel. Subsequently, the air-fuel mixture is then burned in the combustion zone of the combustion chamber 5 to form the working medium.
- FIG. 3 a swirl generator of the burner 6 is shown in a perspective view.
- the swirl generator 31 has a central fuel distributor element 37 which is surrounded by an outer wall 39, which forms an axial flow channel for compressor air.
- a partition wall 42 surrounding the central fuel distributor element 37 and located radially inside the outer wall 39 is also present, which separates the flow channel 41 into a radially inner channel section 43 and a radially outer channel section 45.
- swirl vanes 47 extend in the radial direction through the radially outer channel section to the outer wall 39. The swirl vanes 47 impart a tangential flow component to the compressor air flowing through the radially outer channel section 45, so that the air after passing through the swirl generator 31 forms a vortex.
- the pipelines 49 may in principle also have a round cross-section.
- the fuel conduits 49 are arranged to be aligned with the swirl vanes 47 in the radially outer passage portion so that a fuel passage 51 may extend in a straight line from the central fuel distributor 37 through the fuel conduits 49 to the swirl vanes 47.
- the fuel channels 51 are in particular in FIG. 5 which shows a sectional view through the swirl generator 31 along its longitudinal axis.
- outlet openings 53 in the swirl vanes 47 and outlet openings 55 in the fuel pipes 49 are supplied with fuel.
- the outlet openings 53, 55 are arranged so that the fuel is injected substantially perpendicular to the flow direction of the compressor air in the radially outer channel portion 45 and the radially inner channel portion 43.
- the swirl generator design described causes the compressor air flowing through the radially inner channel section 43 to be imparted with no twist. As a result, the flow velocity of this compressor air in the axial direction is higher than in the compressor air flowing through the radially outer channel section 45, in which part of the axial flow is converted into a tangential flow component. Due to the higher axial flow rate in the radially inner channel portion, ie, in the area adjacent to the central fuel distribution element 37, the emergence of low axial flow rate zones downstream of the central fuel distribution element 37 can be avoided, which in turn results in avoiding flashbacks. This allows more fuel to be injected in the vicinity of the central distributor element 37 compared to the prior art, which reduces the NO x emissions during combustion.
- the partition 42 extends at least over the entire axial length of the swirl vanes 47 in the radially outer channel section 45, so that the supply of a tangential flow component in the radially inner channel section 43 can be reliably avoided.
- the partition wall 42 also extends in the axial direction beyond the arrival and trailing edges of the swirl vanes 47 in order to avoid influencing the compressor air flowing through the radially inner channel section 43 by the swirling air flowing in the radially outer channel section 45.
- FIG. 6 An alternative embodiment of the swirl generator 31 is shown in FIG. 6 shown. Elements corresponding to the swirl generator of the first embodiment are shown in FIG FIG. 6 are denoted by the same reference numerals as in the first embodiment and will not be explained again to avoid repetition.
- the swirl generator 131 of the second embodiment differs from the swirl generator 31 of the first embodiment only by its partition wall 142.
- the partition wall 142 of the second embodiment has a conical portion 144 which causes the opening cross section of the radially inner channel portion 43 reduced toward the output of the swirl generator 131 out.
- the conical portion 144 By the conical portion 144, the flow velocity of the compressor air flowing through the radially inner passage portion 43 increases in comparison with the swirl generator 31 of the first embodiment.
- the central fuel distributor element 37 can thus be surrounded by an air jacket, which has a particularly high axial flow velocity and thus particularly reliably avoids the formation of regions with low flow velocity, and consequently the formation of flashbacks.
- the partition 142 in the present embodiment only has a conical portion 144 downstream, it may also be conical over its entire axial length.
- FIG. 7 A third embodiment of the swirl generator according to the invention is in FIG. 7 shown in a partially sectioned view. As with the swirl generator of the second embodiment, even in the swirl generator of the third embodiment, all those elements which do not differ from the first embodiment are denoted by the same reference numerals as in the first embodiment and will not be described again.
- the swirl generator 231 of the third exemplary embodiment differs from the swirl generator of the first exemplary embodiment in that swirl blades 149 are also present in the radially inner channel section 43.
- swirl blades 47 in the radially outer channel section 45 suction side and pressure side of the blades are reversed, so that the compressor air in the radially inner channel section through the compressor blades 159 a tangential component is taught, which has a reverse orientation with respect to the axial flow direction than the tangential component, which is imparted to the compressor air in the radially outer channel section 45 by the swirl blades 47 located there. Also by this measure can be avoided flashbacks.
- the swirl vanes 149 in the radially inner passage section 43 have fuel channels 51 and fuel outlets 155 arranged to inject the fuel substantially perpendicular to the flow direction of the air flowing through the radially inner passage section 43.
- FIG. 7 Although the swirler 231 of the third embodiment is shown in FIG. 7 is shown with a cylindrical partition wall 42, the swirl generator according to the third embodiment also be equipped with an at least partially conical partition, as has been described with reference to the second embodiment.
- the partitions do not protrude beyond the downstream end of the respective outer wall.
- the dividing walls can also be extended downstream, as shown in the figures, so that they protrude beyond the downstream end of the outer wall. This applies regardless of whether a partition is conical or not.
- the relatively complex geometric shape of the swirl generator according to the described embodiments can be realized in an advantageous manner when the swirl generators are produced as castings.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
Description
Die vorliegende Erfindung bezieht sich auf einen Drallerzeuger mit einem zentralen Brennstoffverteilerelement und auf einen Brenner mit wenigstens einem Drallerzeuger. Daneben betrifft die Erfindung ein Verfahren zum Vermeiden von Flammenrückschlag (Falshback) in einem Brenner, der wenigstens einen Drallerzeuger mit einem zentralen Brennstoffverteilerelement umfasst.The present invention relates to a swirl generator with a central fuel distributor element and to a burner with at least one swirl generator. In addition, the invention relates to a method for avoiding flashback in a burner comprising at least one swirl generator with a central fuel distributor element.
Gasturbinenbrenner mit einem zentralen Brennstoffverteilerelementen und die Brennstoffverteilerelemente umgebenden Drallerzeugern sind beispielsweise in
Um einen Flammenrückschlag zu vermeiden, ist in
Gegenüber dem zitierten Stand der Technik ist es Aufgabe der vorliegenden Erfindung, einen vorteilhaften Drallerzeuger und einen vorteilhaften Brenner zu schaffen. Weiterhin ist es Aufgabe der vorliegenden Erfindung, ein vorteilhaftes Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner mit wenigstens einem Drallerzeuger zur Verfügung zu stellen.Compared to the cited prior art, it is an object of the present invention to provide an advantageous swirl generator and an advantageous burner. A further object of the present invention is to provide an advantageous method for avoiding flashback in a burner with at least one swirl generator.
Die genannten Aufgaben werden durch einen Drallerzeuger gemäß Anspruch 1, einen Brenner gemäß Anspruch 11 bzw. ein Verfahren zum Vermeiden von Flammenrückschlag nach Anspruch 12 gelöst. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.The above objects are achieved by a swirl generator according to claim 1, a burner according to
Ein erfindungsgemäßer Drallerzeuger umfasst ein zentrales Brennstoffverteilerelement, eine das zentrale Brennstoffverteilerelement umgebende und einen axialen Strömungskanal für Verbrennungsluft begrenzende Außenwand, Drallschaufeln, die sich in radialer Richtung bis zur Außenwand erstrecken und der strömenden Verbrennungsluft eine tangentiale Strömungskomponente aufprägen, sowie eine das zentrale Brennstoffverteilerelement umgebende und radial innerhalb der Außenwand gelegene Trennwand. Die Trennwand trennt den Strömungskanal in einen radial inneren Kanalabschnitt und einen radial äußeren Kanalabschnitt. Hierbei kann sich die Trennwand in axialer Richtung des Drallerzeugers mindestens über die axiale Länge der Drallschaufeln, insbesondere aber auch über deren axiale Länge hinaus erstrecken. Der radial innere Kanalabschnitt lässt die Verbrennungsluft ohne Aufprägen einer tangentialen Strömungskomponente oder unter Aufprägung einer der Orientierung der tangentialen Strömungskomponente im radial äußeren Kanalabschnitt entgegengesetzten tangentialen Strömungskomponente passieren.A swirl generator according to the invention comprises a central fuel distributor element, an outer wall surrounding the central fuel distributor element and defining an axial flow channel for combustion air, swirl vanes extending radially to the outer wall and imparting a tangential flow component to the flowing combustion air, and radially surrounding the central fuel distributor element inside the outer wall partition. The partition separates the flow channel into a radially inner channel section and a radially outer channel section. Here, the partition in the axial direction of the swirl generator at least over the axial length of the swirl blades, but in particular also extend beyond the axial length. The radially inner channel section allows the combustion air to pass through without imparting a tangential flow component or by impinging on one of the orientation of the tangential flow component in the radially outer channel section opposite tangential flow component.
Durch das völlige Vermeiden einer tangentialen Komponente im inneren Kanalbereich lässt sich um das zentrale Brennstoffverteilerelement herum eine diese Element umhüllende Strömung mit hoher axialer Strömungsgeschwindigkeit erzeugen, die einen Flammenrückschlag zuverlässig zu vermeiden hilft. Aber auch das Erzeugen eines Gegendralles im inneren Kanalabschnitt, also eines Dralles, dessen Orientierung dem Drall im äußeren Kanalabschnitt entgegengesetzt ist, kann einen Flammenrückschlag vermeiden helfen, da dadurch die Strömungsverhältnisse im Wirbel abströmseitig des zentralen Brennstoffverteilerelementes positiv beeinflusst werden.By completely avoiding a tangential component in the inner channel region, a flow of high axial flow velocity enveloping this element around the central fuel distributor element can be generated which reliably helps to prevent a flashback. But also the generation of a counter-rotation in the inner channel section, ie a swirl, the orientation of which is opposite to the swirl in the outer channel section, can help prevent flashback as this positively influences the flow conditions in the vortex downstream of the central fuel distributor element.
Das vollständige Vermeiden einer tangentialen Strömungskomponente im inneren Kanalabschnitt lässt sich insbesondere dadurch erreichen, dass in diesem Kanalabschnitt überhaupt keine Drallschaufeln vorhanden sind. Um die im radial äußeren Kanalabschnitt vorhandenen Drallschaufeln mit Brennstoff zu versorgen, können sich dann Brennstoffrohrleitungen durch den radial inneren Kanalabschnitt zu den Drallschaufeln im radial äußeren Kanalabschnitt erstrecken. Zur Vermeidung von Strömungsabrissen an den Brennstoffrohrleitungen weisen diese vorteilhafterweise einen kreisförmigen oder tropfenförmigen Querschnitt auf.The complete avoidance of a tangential flow component in the inner channel section can be achieved in particular in that no swirl vanes are present in this channel section at all. To supply the existing in the radially outer channel section swirl vanes with fuel, then fuel pipes can through the extend radially inner channel portion to the swirl vanes in the radially outer channel portion. To avoid stalls on the fuel pipes, these advantageously have a circular or drop-shaped cross section.
Falls sich im radial inneren Kanalabschnitt Drallschaufeln befinden, die der durch den radial inneren Kanalabschnitt strömenden Verbrennungsluft eine tangentiale Strömungskomponente aufprägen, deren Orientierung der tangentialen Strömungskomponente im radial äußeren Kanalabschnitt entgegengesetzt ist, können sich die Brennstoffleitungen für die im radial äußeren Kanalabschnitt befindlichen Drallschaufeln durch die Drallschaufeln im radial inneren Kanalabschnitt erstrecken, bspw. in Form von Bohrungen durch die Drallschaufeln.If there are swirl vanes in the radially inner channel section, which impose a tangential flow component of the combustion air flowing through the radially inner channel section whose orientation is opposite to the tangential flow component in the radially outer channel section, the fuel lines for the swirl vanes located in the radially outer channel section can pass through the swirl vanes extend in the radially inner channel portion, for example. In the form of holes through the swirl blades.
Um ein besonders gleichförmiges Brennstoffprofil im inneren Kanalabschnitt zu erreichen, ist es vorteilhaft, wenn sich in den Brennstoffrohrleitungen oder den Drallschaufeln im inneren Kanalabschnitt Brennstoffaustrittsöffnungen befinden. Diese können insbesondere so angeordnet sein, dass sie den Brennstoff im Wesentlichen senkrecht zur Strömungsrichtung der Verbrennungsluft im radial inneren Kanalabschnitt in die Verbrennungsluft eindüsen. Ebenso können in den Drallschaufeln im radial äußeren Kanalabschnitt Brennstoffaustrittsöffnungen vorhanden sein, die insbesondere so angeordnet sein können, dass sie den Brennstoff im Wesentlichen senkrecht zur Strömungsrichtung der Verbrennungsluft im radial äußeren Kanalabschnitt in die Verbrennungsluft eindüsen. Dadurch kann ein gleichmäßiges Brennstoffprofil auch im radial äußeren Kanalabschnitt erzielt werden. Die Eindüsrichtung braucht aber nicht notwendigerweise senkrecht zur Strömungsrichtung der Verbrennungsluft zu sein. Vielmehr kommen kann die Eindüsrichtung grundsätzlich frei gewählt werden. Der Brennstoff kann also bspw. alternativ oder zusätzlich zur Zuführung senkrecht zur Strömungsrichtung der Verbrennungsluft auch senkrecht zur Radialrichtung und/oder entgegengesetzt zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft und/oder parallel zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft zugeführt werden. Andere, nicht ausdrücklich genannte Richtungen und Kombinationen sind auch möglich. Dies gilt sowohl für die Brennstoffzufuhr im inneren Kanalabschnitt als auch für die Brennstoffzufuhr im äußeren im äußeren Kanalabschnitt.In order to achieve a particularly uniform fuel profile in the inner channel section, it is advantageous if there are fuel outlet openings in the fuel piping or the swirl blades in the inner channel section. These can in particular be arranged so that they inject the fuel substantially perpendicular to the flow direction of the combustion air in the radially inner channel section in the combustion air. Likewise, in the swirl vanes in the radially outer channel section fuel outlet openings may be present, which may be arranged in particular so that they inject the fuel substantially perpendicular to the flow direction of the combustion air in the radially outer channel section into the combustion air. As a result, a uniform fuel profile can also be achieved in the radially outer channel section. However, the injection direction does not necessarily have to be perpendicular to the flow direction of the combustion air. Rather, the injection direction can basically be chosen freely. Thus, for example, alternatively or in addition to the supply perpendicular to the flow direction of the combustion air, the fuel can also be perpendicular to the radial direction and / or opposite to the flow direction of the air flowing through the flow channel Combustion air and / or are supplied parallel to the flow direction of the flowing through the flow channel combustion air. Other, not expressly named directions and combinations are also possible. This applies both to the fuel supply in the inner channel section and to the fuel supply in the outer in the outer channel section.
Um die axiale Strömungsgeschwindigkeit in der Nähe des zentralen Brennstoffverteilerelementes weiter zu erhöhen, kann die Trennwand wenigstens teilweise eine konische Form besitzen, wobei sich der Öffnungsquerschnitt des radial inneren Kanalabschnitts in Strömungsrichtung der Verbrennungsluft verringert.In order to further increase the axial flow velocity in the vicinity of the central fuel distributor element, the dividing wall may at least partially have a conical shape, wherein the opening cross section of the radially inner channel section decreases in the direction of flow of the combustion air.
In einer Weiterbildung des erfindungsgemäßen Drallerzeugers ragt die Trennwand über das abströmseitige Ende der Außenwand hinaus. Diese Weiterbildung kann sowohl bei einer konisch ausgebildeten Trennwand, als auch bei einer nicht konisch ausgebildeten Trennwand realisiert sein.In a development of the swirl generator according to the invention, the dividing wall projects beyond the outflow-side end of the outer wall. This development can be realized both in a conical partition, as well as in a non-conical partition.
Die im Vergleich zu Drallerzeugern nach dem Stand der Technik relativ komplizierte geometrische Form des erfindungsgemäßen Drallerzeugers lässt sich vorteilhaft realisieren, wenn der Drallerzeuger als Gussteil ausgestaltet ist. Wenn erst einmal ein Gießmodell hergestellt ist, unterscheiden sich die Erzeugungskosten für den erfindungsgemäßen Drallerzeuger als Gussteil nicht wesentlich von den Erzeugungskosten für die Drallerzeuger nach Stand der Technik.The relatively complicated in comparison to swirl generators according to the prior art geometric shape of the swirl generator according to the invention can be advantageously realized when the swirl generator is designed as a casting. Once a casting model is made, the cost of producing the swirl generator of the present invention as a casting is not significantly different from the production cost of prior art swirlers.
Ein erfindungsgemäßer Brenner ist mit wenigstens einem erfindungsgemäßen Drallerzeuger ausgestattet. Dadurch lassen sich die mit Bezug auf den Drallerzeuger beschriebenen Vorteile in einem Brenner, der insbesondere ein Gasturbinenbrenner sein kann, realisieren.An inventive burner is equipped with at least one swirl generator according to the invention. As a result, the advantages described with respect to the swirl generator can be realized in a burner, which in particular can be a gas turbine burner.
Erfindungsgemäß wird außerdem ein Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner, der wenigstens einen Drallerzeuger mit einem zentralen Brennstoffverteilerelement und einer das zentrale Brennstoffverteilerelement umgebenden, einen axialen Strömungskanal für Verbrennungsluft begrenzenden Außenwand umfasst, zur Verfügung gestellt. Der durch den Strömungskanal strömenden Verbrennungsluft wird in einem radial äußeren Kanalbereich eine tangentiale Strömungskomponente vermittelt. In einem radial inneren Bereich wird der durch den Strömungskanal strömenden Verbrennungsluft dagegen keine tangentiale Strömungskomponente oder eine der tangentialen Strömungskomponente im radial äußeren Kanalbereich entgegengesetzte tangentiale Strömungskomponente vermittelt.According to the invention, there is also provided a method of preventing flashback in a burner comprising at least one swirl generator with a central fuel distributor element and an outer wall surrounding the central fuel distribution element and defining a combustion air axial flow channel. The combustion air flowing through the flow channel is imparted a tangential flow component in a radially outer channel region. In contrast, in a radially inner region, the combustion air flowing through the flow channel does not impart a tangential flow component or a tangential flow component opposite the tangential flow component in the radially outer channel region.
Die mit dem erfindungsgemäßen Verfahren erzielbaren Vorteile hinsichtlich der Vermeidung eines Flammenrückschlags sind bereits mit Bezug auf den erfindungsgemäßen Drallerzeuger beschrieben worden. Auf diese Beschreibung wird Bezug genommen, um Wiederholungen zu vermeiden.The advantages which can be achieved with the method according to the invention with regard to avoiding a flashback have already been described with reference to the swirl generator according to the invention. This description is referred to to avoid repetition.
Ein besonders gleichmäßiges Brennstoffprofil kann erzeugt werden, wenn der durch den Strömungskanal strömenden Verbrennungsluft Brennstoff zugeführt wird. Der Brennstoff kann hierbei insbesondere senkrecht zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft und/oder senkrecht zur Radialrichtung beigemischt wird. Auch eine Beimischung im wesentlichen entgegengesetzt zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft und/oder parallel zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft ist alternativ oder als Ergänzung zu den zuvor genannten Varianten möglich.A particularly uniform fuel profile can be generated when fuel is supplied to the combustion air flowing through the flow channel. The fuel can in this case in particular be admixed perpendicular to the flow direction of the combustion air flowing through the flow channel and / or perpendicular to the radial direction. An admixing substantially opposite to the flow direction of the combustion air flowing through the flow channel and / or parallel to the flow direction of the combustion air flowing through the flow channel is possible alternatively or in addition to the aforementioned variants.
Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren.
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Figur 1 zeigt eine Gasturbine in einer stark schematisierten Darstellung. -
Figur 2 zeigt einen Gasturbinenbrenner in einer perspektivischen Darstellung. -
Figur 3 zeigt einen Drallerzeuger des Brenners ausFigur 2 in einer perspektivischen Darstellung. -
Figur 4 zeigt den Drallerzeuger ausFigur 3 in einer teilweise geschnittenen Darstellung. -
zeigt den Drallerzeuger ausFigur 5Figur 3 in einem Schnitt entlang seiner Längsachse. -
zeigt eine alternative Ausgestaltung des Drallerzeugers in einer teilweise geschnittenen Darstellung.Figur 6 -
Figur 7 zeigt eine weitere alternative Ausgestaltung des Drallerzeugers in einer teilweise geschnittenen Darstellung.
-
FIG. 1 shows a gas turbine in a highly schematic representation. -
FIG. 2 shows a gas turbine burner in a perspective view. -
FIG. 3 shows a swirl generator of the burnerFIG. 2 in a perspective view. -
FIG. 4 shows the swirl generatorFIG. 3 in a partially cut representation. -
FIG. 5 shows the swirl generatorFIG. 3 in a section along its longitudinal axis. -
FIG. 6 shows an alternative embodiment of the swirl generator in a partially sectioned view. -
FIG. 7 shows a further alternative embodiment of the swirl generator in a partially sectioned view.
Nachfolgend wird anhand von
Im Betrieb der Gasturbine 1 wird Luft durch einen Lufteinlass 21 in den Verdichterabschnitt 3 eingesaugt. Dort wird die Luft durch die rotierenden Verdichterlaufschaufeln 11 komprimiert und zu den Brennern 6 im Verbrennungsabschnitt 4 geleitet. In den Brennern 6 wird die Luft mit einem gasförmigen oder flüssigen Brennstoff gemischt und die Mischung in den Brennkammern 5 verbrannt. Die unter hohem Druck stehenden heißen Verbrennungsabgase werden dann als Arbeitsmedium dem Turbinenabschnitt 7 zugeführt. Auf ihrem Weg durch den Turbinenabschnitt übertragen die Verbrennungsabgase Impuls auf die Turbinenlaufschaufeln 13, wobei sie entspannen und abkühlen. Schließlich verlassen die entspannten und abgekühlten Verbrennungsabgase den Turbinenabschnitt 7 durch einen Auspuff 23. Der übertragene Impuls führt zu einer Rotationsbewegung des Rotors, die den Verdichter und einen Verbraucher, beispielsweise einen Generator zum Erzeugen elektrischen Stroms oder eine industrielle Arbeitsmaschine antreibt. Die Kränze von Turbinenleitschaufeln 17 dienen dabei als Düsen zum Leiten des Arbeitsmediums, um den Impulsübertrag auf die Turbinenlaufschaufeln 13 zu optimieren.During operation of the gas turbine 1, air is sucked through an
Obwohl der in
Beim Verbrennungsprozess wird Luft aus dem Verdichter durch die Drallerzeuger 31 geleitet, wo sie mit Brennstoff gemischt wird. Anschließend wird das Luft-Brennstoff-Gemisch dann in der Verbrennungszone der Brennkammer 5 verbrannt, um das Arbeitsmedium zu bilden.During the combustion process, air from the compressor is passed through the
In
Im radial inneren Kanalabschnitt 43 sind keine Drallschaufeln vorhanden. Stattdessen erstrecken sich, vom zentralen Brennstoffverteilerelement 37 ausgehend, Brennstoffrohrleitungen 49 in radialer Richtung zur Trennwand 42. Wie insbesondere in
Statt eines tropfenförmigen Querschnittes können die Rohrleitungen 49 grundsätzlich aber auch einen runden Querschnitt aufweisen.Instead of a drop-shaped cross-section, however, the
Die Brennstoffrohrleitungen 49 sind so angeordnet, dass sie mit den Drallschaufeln 47 im radial äußeren Kanalabschnitt fluchten, so dass sich ein Brennstoffkanal 51 in gerader Richtung vom zentralen Brennstoffverteilerelement 37 ausgehend durch die Brennstoffrohrleitungen 49 bis in die Drallschaufeln 47 erstrecken kann. Die Brennstoffkanäle 51 sind insbesondere in
Das beschriebene Drallerzeugerdesign führt dazu, dass der durch den radial inneren Kanalabschnitt 43 strömenden Verdichterluft kein Drall vermittelt wird. Dadurch ist die Strömungsgeschwindigkeit dieser Verdichterluft in Axialrichtung höher als bei der durch den radial äußeren Kanalabschnitt 45 strömenden Verdichterluft, bei der ein Teil der axialen Strömung in eine tangentiale Strömungskomponente umgewandelt wird. Aufgrund der höheren axialen Strömungsgeschwindigkeit im radial inneren Kanalabschnitt, d.h. in dem Bereich, der an das zentrale Brennstoffverteilerelement 37 angrenzt, lässt sich das Entstehen von Zonen mit niedriger axialer Strömungsgeschwindigkeit abströmseitig vom zentralen Brennstoffverteilerelement 37 vermeiden, was wiederum zu einer Vermeidung von Flammenrückschlägen führt. Dies erlaubt es im Vergleich zum Stand der Technik, mehr Brennstoff in der Nähe des zentralen Verteilerelements 37 einzudüsen, was die NOx - Emissionen bei der Verbrennung senkt.The swirl generator design described causes the compressor air flowing through the radially
Die Trennwand 42 erstreckt sich mindestens über die gesamte axiale Länge der Drallschaufeln 47 im radial äußeren Kanalabschnitt 45, so dass das Zuführen einer tangentialen Strömungskomponente im radial inneren Kanalabschnitt 43 zuverlässig vermieden werden kann. Im vorliegenden Ausführungsbeispiel erstreckt sich die Trennwand 42 außerdem in axialer Richtung über die An- und Abströmkanten der Drallschaufeln 47 hinaus, um eine Beeinflussung der durch den radial inneren Kanalabschnitt 43 strömenden Verdichterluft durch die im radial äußeren Kanalabschnitt 45 strömende wirbelnde Luft zu vermeiden.The
Eine alternative Ausführungsvariante des Drallerzeugers 31 ist in
Der Drallerzeuger 131 des zweiten Ausführungsbeispiels unterscheidet sich vom Drallerzeuger 31 des ersten Ausführungsbeispiels lediglich durch seine Trennwand 142. Im Unterschied zum ersten Ausführungsbeispiel weist die Trennwand 142 des zweiten Ausführungsbeispiels einen konischen Abschnitt 144 auf, der dazu führt, dass sich der Öffnungsquerschnitt des radial inneren Kanalabschnitts 43 zum Ausgang des Drallerzeugers 131 hin verringert. Durch den konischen Abschnitt 144 erhöht sich die Strömungsgeschwindigkeit der durch den radial inneren Kanalabschnitt 43 strömenden Verdichterluft im Vergleich zum Drallerzeuger 31 aus dem ersten Ausführungsbeispiel. Das zentrale Brennstoffverteilerelement 37 lässt sich so mit einem Luftmantel umgeben, der eine besonders hohe axiale Strömungsgeschwindigkeit aufweist und so besonders zuverlässig die Bildung von Gebieten mit niedriger Strömungsgeschwindigkeit, und damit einhergehend die Bildung von Flammenrückschläge, vermeidet.The
Obwohl die Trennwand 142 im vorliegenden Ausführungsbeispiel lediglich abströmseitig einen konischen Abschnitt 144 aufweist, kann sie auch über ihre gesamte axiale Länge konisch ausgebildet sein.Although the
Eine dritte Ausführungsvariante des erfindungsgemäßen Drallerzeugers ist in
Der Drallerzeuger 231 des dritten Ausführungsbeispiels unterscheidet sich vom Drallerzeuger des ersten Ausführungsbeispiels dadurch, dass auch im radial inneren Kanalabschnitt 43 Drallschaufeln 149 vorhanden sind. Im Unterschied zu den Drallschaufeln 47 im radial äußeren Kanalabschnitt 45 sind jedoch Saugseite und Druckseite der Schaufeln vertauscht, so dass der Verdichterluft im radial inneren Kanalabschnitt durch die Verdichterschaufeln 159 eine tangentiale Komponente vermittelt wird, die eine umgekehrte Orientierung bezüglich der axialen Strömungsrichtung aufweist, als die tangentiale Komponente, die der Verdichterluft im radial äußeren Kanalabschnitt 45 durch die dort befindlichen Drallschaufeln 47 vermittelt wird. Auch durch diese Maßnahme lassen sich Flammenrückschläge vermeiden. Wie die Brennstoffrohrleitungen 49 in den ersten beiden Ausführungsbeispielen weisen die Drallschaufeln 149 im radial inneren Kanalabschnitt 43 Brennstoffkanäle 51 und Brennstoffaustrittsöffnungen 155 auf, die so angeordnet sind, dass sie den Brennstoff im wesentlichen senkrecht zur Strömungsrichtung der durch den radial inneren Kanalabschnitt 43 strömenden Luft eindüsen.The
Obwohl der Drallerzeuger 231 des dritten Ausführungsbeispiels in
Bei den in den Figuren dargestellten Ausführungsbeispielen ragen die Trennwände nicht über das abströmseitige Ende der jeweiligen Außenwand hinaus. Die Trennwände können jedoch auch - anders als in den Figuren dargestellt - abströmseitig verlängert sein, so dass sie über das abströmseitige Ende der Außenwand hinausragen. Dies gilt unabhängig davon, ob eine Trennwand konisch ausgebildet ist oder nicht.In the embodiments illustrated in the figures, the partitions do not protrude beyond the downstream end of the respective outer wall. However, the dividing walls can also be extended downstream, as shown in the figures, so that they protrude beyond the downstream end of the outer wall. This applies regardless of whether a partition is conical or not.
Die relativ komplexe geometrische Form der Drallerzeuger gemäß den beschriebenen Ausführungsbeispielen lässt sich in vorteilhafter Weise realisieren, wenn die Drallerzeuger als Gussteile hergestellt werden.The relatively complex geometric shape of the swirl generator according to the described embodiments can be realized in an advantageous manner when the swirl generators are produced as castings.
Claims (15)
dadurch gekennzeichnet, dass
sich die Trennwand (42, 142) in axialer Richtung mindestens über die axiale Länge der Drallschaufeln (47) erstreckt.Swirl generator (31, 131, 231) according to claim 1,
characterized in that
the partition wall (42, 142) extends in the axial direction at least over the axial length of the swirl vanes (47).
dadurch gekennzeichnet, dass
sich nur im radial äußeren Kanalabschnitt (45) Drallschaufeln (47) befinden.Swirl generator (31, 131) according to claim 1 or claim 2,
characterized in that
Only in the radially outer channel section (45) swirl vanes (47) are located.
dadurch gekennzeichnet, dass
sich Brennstoffrohrleitungen (49) durch den radial inneren Kanalabschnitt (43) zu den Drallschaufeln (47) im radial äußeren Kanalabschnitt (45) erstrecken.Swirl generator (31, 131) according to one of claims 1 to 3,
characterized in that
Fuel piping (49) through the radially inner channel portion (43) to the swirl blades (47) in the radially outer channel portion (45) extend.
dadurch gekennzeichnet, dass
die Brennstoffrohrleitungen (49) einen kreisförmigen oder tropfenförmigen Querschnitt aufweisenSwirl generator (31, 131) according to claim 4,
characterized in that
the fuel pipes (49) have a circular or drop-shaped cross-section
dadurch gekennzeichnet, dass
sich im radial inneren Kanalabschnitt (43) Drallschaufeln (149) befinden, die der durch den radial inneren Kanalabschnitt (43) strömenden Verbrennungsluft eine tangentiale Strömungskomponente aufprägen, deren Orientierung der tangentialen Strömungskomponente im radial äußeren Kanalabschnitt (45) entgegengesetzt ist, und sich Brennstoffleitungen (51) durch die Drallschaufeln (149) im radial inneren Kanalabschnitt (43) zu den Drallschaufeln (47) im radial äußeren Kanalabschnitt (45) erstrecken.Swirl generator (231) according to claim 1,
characterized in that
there are swirl vanes (149) in the radially inner channel section (43) which impart to the combustion air flowing through the radially inner channel section (43) a tangential flow component whose orientation is opposite to the tangential flow component in the radially outer channel section (45); 51) extend through the swirl vanes (149) in the radially inner channel section (43) to the swirl vanes (47) in the radially outer channel section (45).
dadurch gekennzeichnet, dass
sich in den Brennstoffrohrleitungen (49) oder den Drallschaufeln (149) im inneren Kanalabschnitt (43) Brennstoffaustrittsöffnungen (55, 155) befinden.Swirl generator (31, 131, 231) according to one of claims 4 to 6,
characterized in that
in the fuel pipes (49) or the swirl blades (149) in the inner channel portion (43) fuel outlet openings (55, 155) are located.
dadurch gekennzeichnet, dass
sich in den Drallschaufeln (47) im radial äußeren Kanalabschnitt Brennstoffaustrittsöffnungen (53) befinden.Swirl generator (31, 131, 231) according to one of claims 1 to 7,
characterized in that
in the swirl vanes (47) in the radially outer channel section are fuel outlet openings (53).
dadurch gekennzeichnet, dass
die Trennwand (142) wenigstens teilweise eine konische Form (144) besitzt, wobei sich der Öffnungsquerschnitt des radial inneren Kanalabschnittes (43) in Strömungsrichtung der Verbrennungsluft verringert.Dall generator (131) according to one of claims 1 to 8,
characterized in that
the partition (142) at least partially has a conical shape (144), wherein the opening cross-section of the radially inner channel portion (43) decreases in the direction of flow of the combustion air.
dadurch gekennzeichnet, dass
die Trennwand über das abströmseitige Ende der Außenwand (39) hinausragt.Dall generator (31, 131, 231) according to one of claims 1 to 9,
characterized in that
the partition protrudes beyond the downstream end of the outer wall (39).
gekennzeichnet durch
seine Ausgestaltung als Gussteil.Dall generator (31, 131, 231) according to one of claims 1 to 10,
marked by
its design as a casting.
dadurch gekennzeichnet, dass
der durch den Strömungskanal (41) strömenden Verbrennungsluft in einem radial inneren Kanalbereich (43) keine tangentiale Strömungskomponente oder eine der tangentiale Strömungskomponente im radial äußeren Kanalbereich (45) entgegengesetzte tangentiale Strömungskomponente vermittelt wird.A method for preventing flashback in a burner (6) comprising at least one swirl generator (31, 131, 231) with a central fuel distributor element (37) and an outer wall (39) surrounding the central fuel distributor element and defining a combustion air axial flow channel (41) comprises, in which the combustion air flowing through the flow channel (41) in a radially outer channel region (45) a tangential flow component is mediated,
characterized in that
the flowing through the flow channel (41) combustion air in a radially inner channel region (43) no tangential flow component or a tangential flow component in the radially outer channel region (45) opposite tangential flow component is mediated.
dadurch gekennzeichnet, dass
der durch den Strömungskanal (41) strömenden Verbrennungsluft Brennstoff zugeführt wird.Method according to claim 13,
characterized in that
the combustion air flowing through the flow passage (41) is supplied with fuel.
dadurch gekennzeichnet, dass
der durch den Strömungskanal (41) strömenden Verbrennungsluft Brennstoff senkrecht zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft und/oder senkrecht zur Radialrichtung und/oder entgegengesetzt zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft und/oder parallel zur Strömungsrichtung der durch den Strömungskanal strömenden Verbrennungsluft zugeführt wird.Method according to claim 14,
characterized in that
the combustion air flowing through the flow channel (41) is supplied with fuel perpendicular to the flow direction of the combustion air flowing through the flow channel and / or perpendicular to the radial direction and / or opposite to the flow direction of the combustion air flowing through the flow channel and / or parallel to the flow direction of the combustion air flowing through the flow channel becomes.
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09155904.7A EP2233836B1 (en) | 2009-03-23 | 2009-03-23 | Swirler, method for reducing flashback in a burner with at least one swirler and burner |
JP2010059450A JP5615008B2 (en) | 2009-03-23 | 2010-03-16 | Swirler and burner with at least one swirler |
CA2697200A CA2697200A1 (en) | 2009-03-23 | 2010-03-19 | Swirl generator, method for preventing flashback in a burner having at least one swirl generator and burner |
RU2010110965/06A RU2535901C2 (en) | 2009-03-23 | 2010-03-22 | Swirler, method for prevention of backfire of burner at least with one swirler, and burner |
US12/728,518 US8789373B2 (en) | 2009-03-23 | 2010-03-22 | Swirl generator, method for preventing flashback in a burner having at least one swirl generator and burner |
CN201010151559.6A CN101846320B (en) | 2009-03-23 | 2010-03-23 | Swirl generator, method for preventing flashback in burner and burner |
US14/263,509 US20140230448A1 (en) | 2009-03-23 | 2014-04-28 | Method for preventing flashback in a burner having at least one swirl generator |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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EP09155904.7A EP2233836B1 (en) | 2009-03-23 | 2009-03-23 | Swirler, method for reducing flashback in a burner with at least one swirler and burner |
Publications (2)
Publication Number | Publication Date |
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EP2233836A1 true EP2233836A1 (en) | 2010-09-29 |
EP2233836B1 EP2233836B1 (en) | 2015-07-29 |
Family
ID=40942432
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Application Number | Title | Priority Date | Filing Date |
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EP09155904.7A Not-in-force EP2233836B1 (en) | 2009-03-23 | 2009-03-23 | Swirler, method for reducing flashback in a burner with at least one swirler and burner |
Country Status (6)
Country | Link |
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US (2) | US8789373B2 (en) |
EP (1) | EP2233836B1 (en) |
JP (1) | JP5615008B2 (en) |
CN (1) | CN101846320B (en) |
CA (1) | CA2697200A1 (en) |
RU (1) | RU2535901C2 (en) |
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- 2010-03-19 CA CA2697200A patent/CA2697200A1/en not_active Abandoned
- 2010-03-22 US US12/728,518 patent/US8789373B2/en not_active Expired - Fee Related
- 2010-03-22 RU RU2010110965/06A patent/RU2535901C2/en not_active IP Right Cessation
- 2010-03-23 CN CN201010151559.6A patent/CN101846320B/en not_active Expired - Fee Related
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2014
- 2014-04-28 US US14/263,509 patent/US20140230448A1/en not_active Abandoned
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2685164A1 (en) | 2012-07-10 | 2014-01-15 | Alstom Technology Ltd | Axial swirler for a gas turbine burner |
KR20160022846A (en) | 2012-07-10 | 2016-03-02 | 제네럴 일렉트릭 테크놀러지 게엠베하 | Axial swirler for a gas turbine burner |
US9518740B2 (en) | 2012-07-10 | 2016-12-13 | General Electric Company Gmbh | Axial swirler for a gas turbine burner |
Also Published As
Publication number | Publication date |
---|---|
JP5615008B2 (en) | 2014-10-29 |
US20100236252A1 (en) | 2010-09-23 |
EP2233836B1 (en) | 2015-07-29 |
RU2010110965A (en) | 2011-09-27 |
US20140230448A1 (en) | 2014-08-21 |
CN101846320B (en) | 2014-12-17 |
CA2697200A1 (en) | 2010-09-23 |
JP2010223577A (en) | 2010-10-07 |
US8789373B2 (en) | 2014-07-29 |
CN101846320A (en) | 2010-09-29 |
RU2535901C2 (en) | 2014-12-20 |
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