EP2470834B1 - Burner, in particular for gas turbines - Google Patents
Burner, in particular for gas turbines Download PDFInfo
- Publication number
- EP2470834B1 EP2470834B1 EP10749631.7A EP10749631A EP2470834B1 EP 2470834 B1 EP2470834 B1 EP 2470834B1 EP 10749631 A EP10749631 A EP 10749631A EP 2470834 B1 EP2470834 B1 EP 2470834B1
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- EP
- European Patent Office
- Prior art keywords
- fuel
- distributor
- burner
- supply
- nozzles
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- 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
- F23R3/36—Supply of different fuels
Definitions
- the present invention relates to a burner, and more particularly to a gas turbine combustor having a central fuel supply arrangement.
- the invention relates to a gas turbine.
- burners have been developed in recent years that have particularly low emissions of nitrogen oxides (NOx). It is often emphasized that such burners are not only with a fuel, but possibly with different fuels, such as oil and natural gas, either selectively or in combination operable to increase the security of supply and flexibility of operation. Such burners are for example in the EP 0 276 696 B1 described.
- the in EP 0 276 696 B1 described burner is a hybrid burner for Vormisch plante with gas and / or oil, as it is used in particular for gas turbine plants.
- the burner comprises a central fuel supply assembly, in which a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
- a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
- the central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with therein a swirl blading with a plurality of blades and nozzle pipes for pre-mixing with gas arranged upstream of the blades.
- inlet nozzles for oil in the area of the swirl blading which allow premixing of the main air flow with oil.
- the fuel gas can also be injected into the air duct through nozzle openings arranged in the swirl vanes itself, as described, for example, in US Pat EP 0 580 683 B1 is described.
- a generic burner is in EP 2 161 502 A1 disclosed.
- the object of the present invention is therefore to provide a burner, in particular a gas turbine burner, with two fuel passages which has a long service life. It is a second object of the present invention to provide an advantageous gas turbine.
- the first object is achieved by the disclosure of a burner according to claim 1, the second object by a gas turbine according to claim 7.
- the dependent claims contain advantageous embodiments of the invention.
- a burner has a central fuel supply arrangement and an annular air channel surrounding the central fuel supply arrangement for supplying combustion air.
- swirl vanes are arranged, which first fuel nozzles for injecting a substantially gaseous fuel into the combustion air and second fuel nozzles for injecting a substantially gaseous Have fuel in the combustion air.
- the first fuel nozzles are fed by a fuel distributor supply in the fuel supply arrangement and the second fuel nozzles by a fuel distributor channel in the fuel supply arrangement.
- the burner has a fuel flow direction.
- the fuel distributor supply according to the characterizing part of claim 1 is now formed.
- This causes a spatial separation of the two fuel passages, that is, the supply pipe with the ring attachment and the original fuel distribution channel are spatially separated.
- the original fuel distribution channel is more or less parallel to the supply pipe.
- the ring attachment acts to pull out the high voltages from the component, that is, the fuel supply assembly and distribute it evenly over the component. This results in a defusing of the installation space due to lower voltages.
- the life of the fuel supply assembly is significantly extended. Due to the ring attachment, the original aero design is not or only insignificantly influenced. Also already manufactured machines can be easily provided with such a ring attachment and such a feed tube due to the now easier production and now easier installation.
- the ring attachment preferably comprises a separate pipe connection. This supplies the feed pipe with fuel.
- a plurality of swirl vanes are provided, each of these swirl vanes having a separate feed tube, wherein each of the separate feed tubes is connected to the one ring attachment.
- the first fuel injection is fed by a first manifold and the second fuel injection is fed by a second manifold, the manifold being integrated in the swirl vane, and wherein the swirl vane is split between the first and second manifolds divided into two vane halves.
- the distribution pipes and the respective nozzles are supplied separately with fuel. As a result, a controlled control of the fuel flow is possible.
- Both blade halves preferably have a locating pin downstream and a sliding seat upstream. By the dowel pin and the sliding seat, the two blade halves are now thermally separately expandable, which also stresses are reduced.
- the fuel distribution channel and the supply pipe are separated by a web, wherein the web is made flexible.
- the web can be made of an elastic material and / or also act by a corresponding geometric design elastic and thus compensate for stress. This can e.g. be effected by a curved or corrugated web.
- such a burner is provided in a gas turbine.
- FIG. 1 shows a burner in a highly schematic schematic diagram, the concept underlying the burner.
- the burner which may optionally be used in conjunction with a plurality of similar burners, for example in the combustion chamber of a gas turbine plant, comprises an inner pilot burner system and a main burner system concentrically surrounding the pilot burner system. Both the pilot burner system and the main burner system may optionally be operated with gaseous and / or liquid fuels, such as natural gas or fuel oil.
- the pilot burner system includes an inner oil supply passage 1 which may be concentrically surrounded by an inner annular gas supply passage 3. This in turn can be from an inner Air supply channel or Inertstoffzubuchkanal 5 concentrically surrounded.
- a suitable ignition system may be arranged in or on this air supply channel (not shown in the figure).
- the pilot burner system has a combustion chamber 7 zuwerende outlet opening 9, in whose area a twist blading 11 may be arranged in the air supply duct. Gas can be injected from the inner gas supply channel 3 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 5 by means of nozzle openings 13. Oil from the oil supply channel can be injected by means of oil nozzles 15 downstream of the swirl blading into the supplied air or the supplied inert material.
- the pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame.
- a diffusion burner in which the fuel is injected directly into the flame.
- the pilot burner system it is also possible to operate the pilot burner system as a premix burner, in which the fuel is thoroughly mixed with air before the mixture is fed to the flame.
- the main burner system surrounding the pilot burner system comprises a radial outer air supply channel 17, also called an annular air channel, through which swirl blades 19 of a swirl blading extend.
- These swirl blades 19 have first fuel nozzles 21 and second fuel nozzles 23, through which fuel gas can be injected into the air flowing in through the radial air supply channel 17.
- air can also be injected by means of oil nozzles 25 oil.
- the first fuel nozzles 21 and second fuel nozzles 23 located in the swirl vanes 19 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 27.
- the Swirl vane 19 and the hub 27 have a fuel flow direction.
- this first and second annular fuel distributor channels 29 and 31 are arranged, which supply the fuel nozzles 21 and 23 with gas.
- an annular oil distribution channel 33 is arranged, which supplies the oil nozzles 25 with oil.
- the fuel distribution channels 29, 31 and the oil distribution channel 33 are supplied via fuel supply channels 35, 37 or via an oil supply channel 39 with the appropriate fuel.
- the fuel supply channels 35, 37 supply the fuel distribution channels 29, 31 with fuel.
- For the oil supply channel 39 is a separate oil supply pipe 43 before.
- FIG. 2 shows a schematic diagram of a swirl blade 19 with two integrated gas stages B and D.
- the swirl blade 19 has two independent fuel distributor channels 29 and 31.
- the one fuel distribution channel 29 with the outlet nozzles 21 can be used, for example, for injecting a different medium D than the second fuel distribution channel 31 via the outlet nozzles 23 (medium B).
- both be injected through the fuel distribution channels 29 and 31 of the swirl vane 19 media gaseous, z.
- an inert material such as water vapor can be injected via these outlet nozzles 21 and / or 23 if necessary.
- FIG. 3 shows a fuel hub 27 with the fuel distribution channel 29 and 31 with openings, which leads the fuel into the blade 19.
- the two fuel distribution channels 29 and 31 are arranged substantially parallel and separated by a web 50.
- At least one of the fuel distributor channels 29 is now designed as a feed tube 55 ( Fig. 4 ).
- the feed tube 55 opens downstream into a manifold 65 (or alternatively 70). Upstream is the feed tube 55 with the ring attachment 60 (FIG. Fig. 5 ) connected.
- the ring attachment 60 seen in the flow direction, the fuel distribution channel 31 (or alternatively 29) upstream.
- the original fuel distribution channel 31 is parallel to the supply pipe 55.
- the ring attachment 60 is supplied with a separate pipe connection 75.
- the original fuel distribution channel 31 (or alternatively 29) is supplied with another channel 80.
- the two leading gas passages namely the feed tube 55 with the ring attachment 60 and the original fuel distribution channel 31 (or alternatively 29) according to the invention spatially decoupled.
- the ring attachment 60 acts to pull the high stresses out of the hub 27 and distribute them evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the burner hub 27 is substantially extended.
- the ring attachment 60 does not or only insignificantly influences the original aero design. Also already manufactured machines can easily be provided with such a ring attachment 60 and such a feed tube 55 due to the now easier production and now easier installation.
- Such a burner hub 27 is preferably used in conjunction with a split swirl blade 19.
- This comprises the first fuel injection 21, which is fed by a first distributor pipe 65, and the second fuel injection 23, which is fed by a second distributor pipe 70.
- the manifold 65, 70 integrated in the swirl blade 19.
- the split swirl vane 19 is now interposed between the first and second manifolds 65 and 70 divided into two vane halves 19a, 19b.
- the blade halves 19a, 19b also have downstream of a fitting pin 90a, 90b and upstream of a sliding seat 85a, 85b, which is mounted so to speak in the hub 27 itself.
- the web 50 in order to obtain an additional voltage reduction, can be made flexible.
- the web 50 can be made of an elastic material. Additionally or alternatively, the web 50 can also act elastically by a corresponding geometry and thus compensate for stresses. This can e.g. be effected by a curved or corrugated web 50.
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Description
Die vorliegende Erfindung betrifft einen Brenner und insbesondere einen Gasturbinenbrenner mit einer zentralen Brennstoffzufuhranordnung. Daneben betrifft die Erfindung eine Gasturbine.The present invention relates to a burner, and more particularly to a gas turbine combustor having a central fuel supply arrangement. In addition, the invention relates to a gas turbine.
Im Hinblick auf die weltweiten Bemühungen zur Senkung des Schadstoffausstoßes von Befeuerungsanlagen, insbesondere bei Gasturbinen, wurden in den letzten Jahren Brenner entwickelt, die besonders geringe Ausstöße an Stickoxiden (NOx) aufweisen. Dabei wird vielfach Wert darauf gelegt, dass solche Brenner jeweils nicht nur mit einem Brennstoff, sondern möglichst mit verschiedenen Brennstoffen, beispielsweise Öl und Erdgas wahlweise oder in Kombination betreibbar sind, um die Versorgungssicherheit und Flexibilität des Betriebs zu erhöhen. Solche Brenner sind beispielsweise in der
Der in
Um die Kontrolle der Emissionen und der Verbrennungsstabilität zukünftig noch zu erhöhen, soll zusätzlich zu einer Brennstoffeindüsung durch die Schaufel wie in
Aufgabe der vorliegenden Erfindung ist es daher, einen Brenner, insbesondere einen Gasturbinenbrenner, zur Verfügung zu stellen mit zwei Brennstoffpassagen, welcher eine lange Lebensdauer aufweist. Es ist eine zweite Aufgabe der vorliegenden Erfindung, eine vorteilhafte Gasturbine zur Verfügung zu stellen.The object of the present invention is therefore to provide a burner, in particular a gas turbine burner, with two fuel passages which has a long service life. It is a second object of the present invention to provide an advantageous gas turbine.
Die erste Aufgabe wird durch die Angabe eines Brenners nach Anspruch 1 gelöst, die zweite Aufgabe durch eine Gasturbine nach Anspruch 7. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.The first object is achieved by the disclosure of a burner according to claim 1, the second object by a gas turbine according to claim 7. The dependent claims contain advantageous embodiments of the invention.
Dabei weist ein Brenner eine zentrale Brennstoffzufuhranordnung und einen die zentrale Brennstoffzufuhranordnung umgebenden Ringluftkanal zur Zufuhr von Verbrennungsluft auf. In dem Ringluftkanal sind Drallschaufeln angeordnet, welche erste Brennstoffdüsen zum Eindüsen eines im Wesentlichen gasförmigen Brennstoffs in die Verbrennungsluft und zweite Brennstoffdüsen zum Eindüsen eines im Wesentlichen gasförmigen Brennstoffs in die Verbrennungsluft aufweisen. Dabei werden die ersten Brennstoffdüsen von einer Brennstoffverteilerzufuhr in der Brennstoffzufuhranordnung gespeist und die zweiten Brennstoffdüsen von einem Brennstoffverteilerkanal in der Brennstoffzufuhranordnung. Im Betrieb weist der Brenner eine Brennstoff Strömungsrichtung auf.In this case, a burner has a central fuel supply arrangement and an annular air channel surrounding the central fuel supply arrangement for supplying combustion air. In the annular air duct swirl vanes are arranged, which first fuel nozzles for injecting a substantially gaseous fuel into the combustion air and second fuel nozzles for injecting a substantially gaseous Have fuel in the combustion air. In this case, the first fuel nozzles are fed by a fuel distributor supply in the fuel supply arrangement and the second fuel nozzles by a fuel distributor channel in the fuel supply arrangement. In operation, the burner has a fuel flow direction.
Erfindungsgemäß wurde nun erkannt, dass für diese doppelte Schaufeleindüsung deshalb eine Realisierung schwierig ist, da keine ausreichende Lebensdauer für den Gasverteiler, das heißt die Brennstoffzufuhranordnung, vorhanden ist und somit kein sicherer Einsatz gewährleistet werden kann. Weiterhin wurde erkannt, dass hohe Temperaturgradienten zwischen den einzelnen Brennstoffpassagen zu hohen Thermospannungen führen, welche die Lebensdauer stark einschränken.According to the invention it has now been recognized that for this double Schaufeleindüsung therefore a realization is difficult because no sufficient life for the gas distributor, that is, the fuel supply arrangement, is present and thus no safe use can be guaranteed. Furthermore, it was recognized that high temperature gradients between the individual fuel passages lead to high thermal stresses, which severely limit the service life.
Erfindungsgemäß ist nun die Brennstoffverteilerzufuhr gemäß dem Kennzeichen von Anspruch 1 ausgebildet. Dies bewirkt eine räumliche Trennung der beiden Brennstoffpassagen, das heißt, das Zufuhrrohr mit dem Ringaufsatz und der ursprüngliche Brennstoffverteilerkanal sind räumlich getrennt. Somit ist der ursprüngliche Brennstoffverteilerkanal quasi parallel zu dem Zufuhrrohr. Der Ringaufsatz wirkt dahingehend, dass er die hohen Spannungen aus dem Bauteil, das heißt, der Brennstoffzufuhranordnung herauszieht und gleichmäßig über dem Bauteil verteilt. Dadurch ergibt sich eine Entschärfung des Bauraums durch niedrigere Spannungen. Somit wird die Lebensdauer der Brennstoffzufuhranordnung wesentlich verlängert. Durch den Ringaufsatz wird das ursprüngliche Aero-Design nicht oder nur unwesentlich beeinflusst. Auch können bereits gefertigte Maschinen leicht mit einem solchen Ringaufsatz und einem solchen Zufuhrrohr aufgrund der nun leichteren Fertigung und des nun leichteren Einbaus versehen werden.According to the fuel distributor supply according to the characterizing part of claim 1 is now formed. This causes a spatial separation of the two fuel passages, that is, the supply pipe with the ring attachment and the original fuel distribution channel are spatially separated. Thus, the original fuel distribution channel is more or less parallel to the supply pipe. The ring attachment acts to pull out the high voltages from the component, that is, the fuel supply assembly and distribute it evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the fuel supply assembly is significantly extended. Due to the ring attachment, the original aero design is not or only insignificantly influenced. Also already manufactured machines can be easily provided with such a ring attachment and such a feed tube due to the now easier production and now easier installation.
Bevorzugt umfasst der Ringaufsatz einen separaten Rohranschluss. Dieser versorgt das Zufuhrrohr mit Brennstoff.The ring attachment preferably comprises a separate pipe connection. This supplies the feed pipe with fuel.
In bevorzugter Ausgestaltung sind mehrere Drallschaufeln vorgesehen, wobei jede einzelne dieser Drallschaufeln ein separates Zufuhrrohr aufweist, wobei jedes der separaten Zufuhrrohre mit dem einen Ringaufsatz verbunden ist.In a preferred embodiment, a plurality of swirl vanes are provided, each of these swirl vanes having a separate feed tube, wherein each of the separate feed tubes is connected to the one ring attachment.
Bevorzugt wird die erste Brennstoffeindüsung von einem ersten Verteilerrohr gespeist und die zweite Brennstoffeindüsung von einem zweiten Verteilerrohr gespeist, wobei das Verteilerrohr in der Drallschaufel integriert ist und wobei die Drallschaufel zwischen dem ersten und zweiten Verteilerrohr geteilt in zwei Schaufelhälften ausgeführt ist. Somit sind die Verteilerrohre und die jeweiligen Düsen getrennt mit Brennstoff versorgbar. Dadurch ist eine geregelte Steuerung des Brennstoffflusses möglich.Preferably, the first fuel injection is fed by a first manifold and the second fuel injection is fed by a second manifold, the manifold being integrated in the swirl vane, and wherein the swirl vane is split between the first and second manifolds divided into two vane halves. Thus, the distribution pipes and the respective nozzles are supplied separately with fuel. As a result, a controlled control of the fuel flow is possible.
Bevorzugt weisen beide Schaufelhälften stromabwärts einen Passzapfen und stromaufwärts einen Schiebesitz auf. Durch die Passzapfen und den Schiebesitz sind die beiden Schaufelhälften nun thermisch separat dehnbar, wodurch ebenfalls Spannungen reduziert werden.Both blade halves preferably have a locating pin downstream and a sliding seat upstream. By the dowel pin and the sliding seat, the two blade halves are now thermally separately expandable, which also stresses are reduced.
In bevorzugter Ausgestaltung sind der Brennstoffverteilerkanal und das Zufuhrrohr durch einen Steg getrennt, wobei der Steg flexibel ausgeführt ist. Dadurch sind auftretende Spannungen im Steg und in der Brennstoffzufuhranordnung reduzierbar. Der Steg kann dabei aus einem elastischen Werkstoff gefertigt sein und/oder aber auch durch eine entsprechende geometrische Gestaltung elastisch wirken und somit Spannungen kompensieren. Dies kann z.B. durch einen gekrümmten oder gewellten Steg bewirkt werden.In a preferred embodiment, the fuel distribution channel and the supply pipe are separated by a web, wherein the web is made flexible. As a result, occurring stresses in the web and in the fuel supply arrangement can be reduced. The web can be made of an elastic material and / or also act by a corresponding geometric design elastic and thus compensate for stress. This can e.g. be effected by a curved or corrugated web.
Bevorzugt ist ein solcher Brenner in einer Gasturbine vorgesehen.Preferably, such a burner is provided in a gas turbine.
Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren.Further features, properties and advantages of the present invention will become apparent from the following description of embodiments with reference to the accompanying figures.
Darin zeigen
- FIG 1
- einen Brenner in einer stark schematisierten Prinzipskizze,
- FIG 2
- eine Prinzipdarstellung einer Drallschaufel mit zwei integrierten Gasstufen,
- FIG 3
- eine Prinzipdarstellung einer Brennkammer-Nabe mit zwei integrierten Gasstufen und einem Ölkanal,
- FIG 4
- einen Querschnitt einer erfindungsgemäßen Brennkammer-Nabe mit Ringaufsatz und Drallschaufel,
- FIG 5
- eine Draufsicht auf einen Ringaufsatz mit Drallschaufeln.
- FIG. 1
- a burner in a very schematized schematic diagram,
- FIG. 2
- a schematic representation of a swirl blade with two integrated gas levels,
- FIG. 3
- a schematic diagram of a combustion chamber hub with two integrated gas stages and an oil channel,
- FIG. 4
- a cross section of a combustion chamber hub according to the invention with ring attachment and swirl blade,
- FIG. 5
- a plan view of a ring attachment with swirl vanes.
Nachfolgend wird mit Bezug auf
Der Brenner, der ggf. in Verbindung mit mehreren gleichartigen Brennern beispielsweise in der Brennkammer einer Gasturbinenanlage eingesetzt werden kann, umfasst ein inneres Pilotbrennersystem und ein das Pilotbrennersystem konzentrisch umgebendes Hauptbrennersystem. Sowohl Pilotbrennersystem als auch Hauptbrennersystem können wahlweise mit gasförmigen und/oder flüssigen Brennstoffen, wie bspw. Erdgas oder Heizöl, betrieben werden.The burner, which may optionally be used in conjunction with a plurality of similar burners, for example in the combustion chamber of a gas turbine plant, comprises an inner pilot burner system and a main burner system concentrically surrounding the pilot burner system. Both the pilot burner system and the main burner system may optionally be operated with gaseous and / or liquid fuels, such as natural gas or fuel oil.
Das Pilotbrennersystem umfasst einen inneren Ölzufuhrkanal 1, der von einem inneren ringförmigen Gaszufuhrkanal 3 konzentrisch umgeben sein kann. Dieser kann wiederum von einem inneren Luftzufuhrkanal oder Inertstoffzufuhrkanal 5 konzentrisch umgeben sein. In oder an diesem Luftzufuhrkanal kann zudem ein geeignetes Zündsystem angeordnet sein (in der Figur nicht dargestellt). Das Pilotbrennersystem weist eine einer Brennkammer 7 zuzuwendende Austrittsöffnung 9 auf, in deren Bereich eine Drallbeschaufelung 11 im Luftzufuhrkanal angeordnet sein kann. Mittels Düsenöffnungen 13 kann Gas aus dem inneren Gaszufuhrkanal 3 im Bereich der Drallbeschaufelung oder stromauf der Drallbeschaufelung in den Luftzufuhrkanal 5 eingedüst werden. Öl aus dem Ölzufuhrkanal kann mittels Öldüsen 15 stromab der Drallbeschaufelung in die zugeführte Luft bzw. den zugeführten Inertstoff eingedüst werden.The pilot burner system includes an inner oil supply passage 1 which may be concentrically surrounded by an inner annular
Das Pilotbrennersystem kann in an sich bekannter Weise mit Öl und/oder Gas als Diffusionsbrenner betrieben werden, in dem der Brennstoff direkt in die Flamme eingedüst wird. Es besteht aber auch die Möglichkeit, das Pilotbrennersystem als Vormischbrenner zu betreiben, in dem der Brennstoff gründlich mit Luft vermischt wird, bevor das Gemisch der Flamme zugeführt wird.The pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame. However, it is also possible to operate the pilot burner system as a premix burner, in which the fuel is thoroughly mixed with air before the mixture is fed to the flame.
Das das Pilotbrennersystem umgebende Hauptbrennersystem umfasst einen radialen äußeren Luftzufuhrkanal 17, auch Ringluftkanal genannt, durch den sich Drallschaufeln 19 einer Drallbeschaufelung erstrecken. Diese Drallschaufeln 19 weisen erste Brennstoffdüsen 21 und zweite Brennstoffdüsen 23 auf, durch die Brenngas in die durch den radialen Luftzufuhrkanal 17 einströmende Luft eingedüst werden kann. In die durch den Luftzufuhrkanal 17 strömende Luft kann mittels Öldüsen 25 zudem Öl eingedüst werden. Zwar ist im vorliegenden Ausführungsbeispiel von Öl und Öldüsen die Rede, jedoch soll dies lediglich stellvertretend für geeignete flüssige Brennstoffe und entsprechende Düsen stehen.The main burner system surrounding the pilot burner system comprises a radial outer
Die in den Drallschaufeln 19 befindlichen ersten Brennstoffdüsen 21 und zweiten Brennstoffdüsen 23 sowie die Öldüsen 25 werden über eine radial innen liegende Brennstoffzufuhranordnung, die sogenannte Nabe 27, mit Brennstoff versorgt. Die Drallschaufel 19 und die Nabe 27 weisen eine Brennstoff-Strömungsrichtung auf. In dieser sind erste und zweite ringförmige Brennstoffverteilerkanäle 29 und 31 angeordnet, die die Brennstoffdüsen 21 bzw. 23 mit Gas versorgen. Weiterhin ist in der Nabe 27 ein ringförmiger Ölverteilerkanal 33 angeordnet, der die Öldüsen 25 mit Öl versorgt. Die Brennstoffverteilerkanäle 29, 31 sowie der Ölverteilerkanal 33 werden über Brennstoffzufuhrkanäle 35, 37 bzw. über einen Ölzufuhrkanal 39 mit dem entsprechenden Brennstoff versorgt. Die Brennstoffzufuhrkanäle 35, 37 versorgen die Brennstoffverteilerkanäle 29, 31 mit Brennstoff. Für den Ölzufuhrkanal 39 liegt ein eigenes Ölzufuhrrohr 43 vor.The
Die Drallschaufel 19 weist zwei voneinander unabhängige Brennstoffverteilerkanäle 29 und 31 auf. Der eine Brennstoffverteilerkanal 29 mit den Auslassdüsen 21 kann beispielsweise zum Eindüsen eines anderen Mediums D als der zweite Brennstoffverteilerkanal 31 über die Auslassdüsen 23 (Medium B) verwendet werden. Vorzugsweise werden beide durch die Brennstoffverteilerkanäle 29 und 31 der Drallschaufel 19 einzudüsenden Medien gasförmig sein, z. B. das eine Medium Erdgas und das andere Medium Kohlegas. Ebenso kann über diese Auslassdüsen 21 und/oder 23 bei Bedarf ein Inertstoff wie etwa Wasserdampf eingedüst werden.The
Erfindungsgemäß wurde nun erkannt, dass für diese doppelte Schaufeleindüsung deshalb eine Realisierung schwierig ist, da keine ausreichende Lebensdauer für den Gasverteiler, das heißt, der Nabe 27 vorhanden ist und somit kein sicherer Einsatz gewährleistet werden kann. Weiterhin wurde erkannt, dass hohe Temperaturgradienten zwischen den einzelnen Brennstoffpassagen zu hohen Thermospannungen führen, welche die Lebensdauer stark einschränken.According to the invention it has now been recognized that for this double Schaufeleindüsung therefore a realization is difficult because no sufficient life for the gas distributor, that is, the
Erfindungsgemäß wird nun zumindest einer der Brennstoffverteilerkanäle 29 (bzw. alternativ 31) als Zufuhrrohr 55 ausgebildet (
Bevorzugt wird eine solche erfindungsgemäße Brenner-Nabe 27 im Zusammenhang mit einer geteilten Drallschaufel 19 eingesetzt. Diese umfasst die erste Brennstoffeindüsung 21, die von einem ersten Verteilerrohr 65 gespeist wird, sowie die zweiten Brennstoffeindüsung 23, welche von einem zweiten Verteilerrohr 70 gespeist wird. Dabei ist das Verteilerrohr 65, 70 in der Drallschaufel 19 integriert. Die geteilte Drallschaufel 19 ist nun zwischen dem ersten und zweiten Verteilerrohr 65 und 70 geteilt in zwei Schaufelhälften 19a, 19b ausgeführt. Hierdurch kann noch verbessert die Spannung aus der Nabe 27 gezogen werden, und gleichmäßig über dem Bauteil verteilt werden. Die Schaufelhälften 19a, 19b weisen zudem stromabwärts einen Passzapfen 90a, 90b und stromaufwärts einen Schiebesitz 85a, 85b auf, der sozusagen in der Nabe 27 selber angebracht wird. Durch die Passzapfen 90a, 90b und den Schiebesitz 85a, 85b sind die beiden Schaufelhälften 19a, 19b nun thermisch separat dehnbar, wodurch ebenfalls Spannungen reduziert werden.Such a
Um eine zusätzliche Spannungsreduktion zu erhalten, kann der Steg 50, durch welchen der Brennstoffverteilerkanal 31 (bzw. 29) und das Zufuhrrohr 55 getrennt sind, flexibel ausgeführt sein. Der Steg 50 kann dabei aus einem elastischen Werkstoff gefertigt sein. Zusätzlich oder alternativ kann der Steg 50 aber auch durch eine entsprechende Geometrie elastisch wirken und somit Spannungen kompensieren. Dies kann z.B. durch einen gekrümmten oder gewellten Steg 50 bewirkt werden.In order to obtain an additional voltage reduction, the
Claims (7)
- Burner with a central fuel supply arrangement (27), an annular air duct (17), surrounding the central fuel supply arrangement (27), for supplying combustion air and swirl vanes (19) which are arranged in the annular air duct (17) and which have first fuel nozzles (21) for injecting an essentially gaseous fuel into the combustion air and second fuel nozzles (23) for injecting an essentially gaseous fuel into the combustion air, wherein the first fuel nozzles (21) are fed by a fuel distributor supply in the fuel supply arrangement (27) and the second fuel nozzles (23) are fed by a fuel distributor duct (31) in the fuel supply arrangement (27), wherein the burner has, in operation, a fuel flow direction,
characterized in that
the fuel distributor supply comprises multiple supply pipes (55), wherein each supply pipe (55) is connected downstream with the first fuel nozzles (21) of in each case one swirl vane (19) and upstream with an annular attachment (60), and wherein the annular attachment (60) is connected upstream of the fuel distributor duct (31) and is fitted on the fuel supply arrangement (27) such that the spatial decoupling between the annular attachment (60) and the fuel distributor duct (31) leads to low stresses in the fuel supply arrangement (27). - Burner according to Claim 1,
characterized in that
the annular attachment (60) comprises a separate pipe connection (75). - Burner according to either of the preceding claims,
characterized in that
the first fuel injection (21) is fed by a first distributor pipe (65) and the second fuel injection (23) is fed by a second distributor pipe (70), wherein the distributor pipe (65, 70) is integrated into the swirl vane and wherein the swirl vane (19) is split into two vane halves (19a, 19b) between the first and second distributor pipes (65, 70). - Burner according to Claim 3,
characterized in that
both vane halves (19a, 19b) have, downstream, a locating pin (90a, 90b). - Burner according to Claim 4,
characterized in that
both vane halves (19a, 19b) have, upstream, a sliding fit (85a, 85b). - Burner according to Claim 1,
characterized in that
the fuel distributor duct (31) and the supply pipe (55) are separated by a web (50), wherein the web (50) is made so as to be flexible such that it is possible to reduce any stresses arising in the web (50). - Gas turbine with at least one burner according to one of the preceding claims.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910038848 DE102009038848A1 (en) | 2009-08-26 | 2009-08-26 | Burner, in particular for gas turbines |
PCT/EP2010/062284 WO2011023669A1 (en) | 2009-08-26 | 2010-08-24 | Burner, in particular for gas turbines |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2470834A1 EP2470834A1 (en) | 2012-07-04 |
EP2470834B1 true EP2470834B1 (en) | 2015-07-15 |
Family
ID=43125513
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10749631.7A Not-in-force EP2470834B1 (en) | 2009-08-26 | 2010-08-24 | Burner, in particular for gas turbines |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP2470834B1 (en) |
CN (1) | CN102597631B (en) |
DE (1) | DE102009038848A1 (en) |
RU (1) | RU2536465C2 (en) |
WO (1) | WO2011023669A1 (en) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8978384B2 (en) * | 2011-11-23 | 2015-03-17 | General Electric Company | Swirler assembly with compressor discharge injection to vane surface |
US9217570B2 (en) * | 2012-01-20 | 2015-12-22 | General Electric Company | Axial flow fuel nozzle with a stepped center body |
CN104471317B (en) | 2012-08-06 | 2016-09-07 | 西门子公司 | Air in the burner with the eddy flow maker with overlapping blades end in perimeter and the local improvement of fuel mixing |
DE102012213852A1 (en) | 2012-08-06 | 2014-02-06 | Siemens Aktiengesellschaft | Burner for use in combustion chamber of gas turbines, has vortex generating elements which are arranged in air supply- and premixing channel on outer shell in areas between swirl blades |
EP2703622B1 (en) | 2012-08-31 | 2014-12-31 | Caterpillar Motoren GmbH & Co. KG | Cylinder head with sensor sleeve |
CN103528094B (en) * | 2013-07-10 | 2015-04-08 | 辽宁省燃烧工程技术中心(有限公司) | Dry-type low-nitrogen combustion device for gas fuel of gas turbine |
DE102015205069B4 (en) * | 2015-03-20 | 2020-04-23 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Incinerator |
DE102015206227A1 (en) * | 2015-04-08 | 2016-10-13 | Siemens Aktiengesellschaft | burner arrangement |
CN109237514B (en) * | 2018-08-08 | 2024-02-23 | 中国华能集团有限公司 | Double-pipeline gas fuel burner for gas turbine |
CN110454781A (en) * | 2019-08-20 | 2019-11-15 | 广东万和电气有限公司 | A kind of air distribution disk and cooker burner |
CN114110662B (en) * | 2021-11-25 | 2023-02-10 | 同济大学 | Low-nitrogen combustion chamber of gas turbine |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3860569D1 (en) * | 1987-01-26 | 1990-10-18 | Siemens Ag | HYBRID BURNER FOR PRE-MIXING OPERATION WITH GAS AND / OR OIL, ESPECIALLY FOR GAS TURBINE PLANTS. |
DE59204270D1 (en) * | 1991-04-25 | 1995-12-14 | Siemens Ag | BURNER ARRANGEMENT, ESPECIALLY FOR GAS TURBINES, FOR LOW POLLUTANT COMBUSTION OF COAL GAS AND OTHER FUELS. |
DE19549140A1 (en) * | 1995-12-29 | 1997-07-03 | Asea Brown Boveri | Method for operating a gas turbine group with low-calorific fuel |
EP1394471A1 (en) * | 2002-09-02 | 2004-03-03 | Siemens Aktiengesellschaft | Burner |
EP1507119A1 (en) * | 2003-08-13 | 2005-02-16 | Siemens Aktiengesellschaft | Burner and process to operate a gas turbine |
US6993916B2 (en) * | 2004-06-08 | 2006-02-07 | General Electric Company | Burner tube and method for mixing air and gas in a gas turbine engine |
EP1614967B1 (en) * | 2004-07-09 | 2016-03-16 | Siemens Aktiengesellschaft | Method and premixed combustion system |
EP1662202B1 (en) * | 2004-11-30 | 2016-11-16 | Siemens Aktiengesellschaft | Burner for a gas turbine |
GB2437977A (en) * | 2006-05-12 | 2007-11-14 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
EP2161502A1 (en) * | 2008-09-05 | 2010-03-10 | Siemens Aktiengesellschaft | Pre-mix burner for a low calorie and high calorie fuel |
-
2009
- 2009-08-26 DE DE200910038848 patent/DE102009038848A1/en not_active Ceased
-
2010
- 2010-08-24 WO PCT/EP2010/062284 patent/WO2011023669A1/en active Application Filing
- 2010-08-24 CN CN201080048392.9A patent/CN102597631B/en not_active Expired - Fee Related
- 2010-08-24 EP EP10749631.7A patent/EP2470834B1/en not_active Not-in-force
- 2010-08-24 RU RU2012111248/06A patent/RU2536465C2/en not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
EP2470834A1 (en) | 2012-07-04 |
CN102597631A (en) | 2012-07-18 |
CN102597631B (en) | 2014-08-13 |
DE102009038848A1 (en) | 2011-03-03 |
WO2011023669A1 (en) | 2011-03-03 |
RU2536465C2 (en) | 2014-12-27 |
RU2012111248A (en) | 2013-10-10 |
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