EP2196734A1 - Fuel lance for a burner - Google Patents

Fuel lance for a burner Download PDF

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Publication number
EP2196734A1
EP2196734A1 EP08171548A EP08171548A EP2196734A1 EP 2196734 A1 EP2196734 A1 EP 2196734A1 EP 08171548 A EP08171548 A EP 08171548A EP 08171548 A EP08171548 A EP 08171548A EP 2196734 A1 EP2196734 A1 EP 2196734A1
Authority
EP
European Patent Office
Prior art keywords
fuel
lance
burner
fuel lance
tip
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.)
Withdrawn
Application number
EP08171548A
Other languages
German (de)
French (fr)
Inventor
Andreas Böttcher
Tobias Krieger
Jürgen MEISL
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08171548A priority Critical patent/EP2196734A1/en
Priority to PCT/EP2009/064664 priority patent/WO2010066516A2/en
Priority to JP2011539985A priority patent/JP5340410B2/en
Priority to US13/133,741 priority patent/US8973367B2/en
Priority to RU2011128704/06A priority patent/RU2529970C2/en
Priority to EP09752330A priority patent/EP2359065A2/en
Priority to CN200980149749.XA priority patent/CN102265091B/en
Publication of EP2196734A1 publication Critical patent/EP2196734A1/en
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/12—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Definitions

  • the present invention relates to a burner lance, for example for a gas turbine combustor, and more particularly to a fuel lance for liquid fuels.
  • Such fuel lances are used for example in burners, which can be operated both with liquid fuel, as well as with gaseous fuel.
  • the lance for operation with the liquid fuels such as oil
  • the oil then flows through the lance and exits at its tip through oil nozzles into a combustion chamber. After exiting the nozzle, the oil in the combustion chamber, in which compressor air is introduced, burned.
  • gaseous fuels are often injected into an air supply channel surrounding the nozzle lance and mixed there with compressor air before the mixture is introduced into the combustion chamber.
  • the lance tip When operated with gaseous fuels, the lance tip is usually exposed to high temperatures in the range of up to about 1000 ° C due to the near flame. These high temperatures can lead to coking of liquid fuel residues in the nozzle lance.
  • a flushing of the fuel passages in the fuel lance with a cooling water Before switching the burner to operate with a liquid fuel is therefore usually a flushing of the fuel passages in the fuel lance with a cooling water to flush away any deposits.
  • the temperature of the cooling water is only about 25 ° C, which can lead to a thermal shock in the hot fuel lance.
  • high temperature gradients develop in the region of the nozzles, so that considerable thermoelectric voltages can occur in the lance tip. The repeated occurrence of such thermal stresses can lead to cracks in the area of the nozzles, as a result of which the starting numbers and thus the service life of the fuel nozzle are reduced.
  • the object of the present invention is therefore to provide a fuel lance for use in a burner, in particular in a gas turbine burner, which helps to overcome the mentioned disadvantages.
  • a further object of the invention is to provide an advantageous firing, in particular a gas turbine burner.
  • the first object is achieved by a fuel lance for a burner, in particular for a gas turbine burner, according to claim 1, the second object by a burner, in particular a gas turbine burner according to claim 8.
  • the dependent claims contain advantageous embodiments of the invention.
  • a burner lance for a burner in particular for a gas turbine burner, comprises a tip which has a nozzle surface with at least two fuel nozzles.
  • the nozzle surface is slotted between the fuel nozzles. It may in particular be formed as an annular surface, such as a conical annular surface, wherein the slots extend perpendicular to the circumferential direction of the annular surface through this.
  • the slits in the nozzle surface allow the lance tip to dissipate thermal stresses through free deformation, thus reducing the thermal gradient of the fuel lance.
  • the slots have no significant aerodynamic influence on the air flowing along the fuel lance or on fuel injected through the fuel nozzles into the airflow.
  • the slots also mean only a minor modification of the fuel lance, which can also be made with very little effort. Therefore, existing fuel lances can be retrofitted with little effort, which increases the possible starting numbers and the life of this fuel lance.
  • the tip cooling air channels may be present, which extend between the fuel nozzles below the nozzle surface.
  • the tip of the fuel lance may be cooled during operation of the burner to minimize the temperature of the tip, thereby further reducing the incidence of thermal stress during purging of the fuel lance.
  • the slots then ideally extend from the nozzle surface to the respective cooling fluid channel. In other words, the slots form passage openings from the nozzle surface to the cooling fluid channel. This embodiment allows a particularly high flexibility of the corresponding material areas for the reduction of thermal voltages.
  • the tip of the fuel lance may be in the shape of a truncated cone.
  • the lateral surface of the truncated cone forms the nozzle surface
  • the cooling fluid channels have at least open outlet openings towards the top surface of the truncated cone.
  • passage openings may be present around the fuel nozzles which are in fluid communication with the air supply channels. Compressor air exiting through these openings can then be used to cool the tip of the lance, in particular in the region of the nozzles to be spooled. In the presence of such passage openings, in particular a respective slot can be arranged in each case between the passage openings of adjacent fuel nozzles.
  • a burner according to the invention which may in particular be a gas turbine burner, is equipped with a fuel lance according to the invention.
  • the fuel lance can be used here for supplying a liquid fuel, wherein in addition to the fuel lance fuel nozzles for gaseous fuels can be present.
  • Fig. 1 shows a section of a burner according to the invention in a sectional view.
  • Fig. 2 shows the tip of the nozzle lance of the burner according to the invention in Fig. 1 in a perspective view.
  • Fig. 3 shows the tip Fig. 2 in a view on her front.
  • a gas turbine burner shown in Fig. 1 .
  • This has one of a substantially cylindrical wall 1 bounded air supply channel 3, in the center of a fuel lance 5 extends.
  • fuel nozzles 7 At the tip of the fuel lance are fuel nozzles 7 for injecting a fuel into the air supplied through the air supply passage 3.
  • the fuel lance 5 is an oil lance for supplying a liquid fuel.
  • the fuel lance burner includes a second fuel supply system 9, which has an axial passage 11 through which the fuel lance 5 is passed, so that only the end portion 13 of the fuel lance 5 protrudes from the fuel supply system 9.
  • the fuel supply system 9 is connected to swirl vanes 15 located at the downstream end of the fuel supply system 9 and extending through the air supply passage 3. through Fuel supply channels 17, a fuel, in the present embodiment, a gaseous fuel, passed into the swirl vanes 15, from where it is injected through nozzle openings 19 in the air flowing through the air supply duct 3 air.
  • the burner shown is a so-called “dual fuel burner", so a burner that can be operated with both gaseous fuels, as well as with liquid fuels.
  • the invention can also be implemented in the context of burners in which both the fuel supply system, and by the fuel lance each a fuel in the same state of matter is supplied, so for example in the context of a burner in which both by the fuel supply system, and by the fuel lance in each case a gaseous fuel is supplied.
  • the fuel lance can be used as a pilot burner.
  • FIG. 2 A perspective view of the end portion 13 of the fuel lance 5 is shown in FIG Fig. 2 shown.
  • Fig. 3 also shows a frontal view of the end portion in the direction along the axial direction of the fuel lance 5.
  • the end portion 13 comprises a substantially cylindrical portion 20, followed by a substantially frusto-conical tip 21 connects.
  • a substantially cylindrical portion 20 In the lateral surface 23 of the frusto-conical tip 21, three fuel nozzles 7 are distributed uniformly in the circumferential direction, in particular Fig. 3 lets recognize. It should be noted at this point, however, that a tip with three fuel nozzles represents only one possible embodiment variant and that more or fewer fuel nozzles or a different distribution of the nozzles in the lateral surface are possible.
  • cooling air channels 25 which open into a central opening 27. This is located where the top surface of the truncated cone runs.
  • the cooling air channels 25 are fed through feed openings 29 in the cylindrical portion 20 of the end portion 13 of the nozzle lance 5.
  • This air has temperatures that are cooler
  • the tip 21 is heated in the gas operation of the illustrated burner by the prevailing flame in the flame chamber to temperatures of about 800 to 1,000 ° C.
  • the fuel passage 31 and the fuel nozzles 7 of the fuel lance 5 are purged to allow coking avoid.
  • This rinsing is typically carried out with water having a temperature of about 25 ° C. Due to the high temperature difference between the rinsing water on the one hand and the tip 21 on the other hand, it comes here in the peak to thermal stresses that are defined breakdown.
  • the nozzle surface forming lateral surface 23 of the tip 21 is provided with slots 33.
  • the slots 33 extend in the present embodiment through the lateral surface 23 through to the cooling air passages 25, so that during operation of the burner cooling air can escape through the slots 33 to lock them against the entry of hot combustion gases.
  • the slots 33 also extend to the feed openings 29. However, they can also be arranged only in the lateral surface 23 of the truncated cone, so that no slot section extends through the cylindrical portion 20.
  • the slots 33 are each arranged in the middle between two fuel nozzles 7 in the present embodiment. Depending on the fluidic conditions in the region of the tip (for example, taking into account the twist generated by the swirl generators 15), however, the slots 33 can also be offset in the clockwise or counterclockwise direction in comparison with the embodiment shown in the FIG. In addition, it is possible to provide a plurality of slots if they extend only through the lateral surface 23 of the truncated cone 21, but not through the cylindrical portion 20. The possible through the slots 33 deformation of the truncated cone surface 23 in the region of the cooling air channels 25 then allows the degradation of the thermal stresses occurring during the rinsing process.
  • optional through holes 30 are present, which extend to the cooling air passages 25 and allow the passage of cooling fluid. In this way, a particularly effective cooling of the material of the lance tip in the region of the nozzle openings to be reeled 7 can be achieved, whereby the thermal shock during flushing and thus the degraded thermoelectric voltages are reduced.
  • the provision of the slots 33 in the fuel lance of the burner according to the invention advantageously allows the removal of thermal stresses during flushing of the fuel lance with rinse water, without the slots adversely affect the aerodynamics in the tip of the fuel lance. Due to the improved reduction of the thermal voltages, the life of the fuel lance is extended. The introduction of the slots in existing fuel lances without slots is also feasible without much effort, so that existing fuel lances can be converted with little effort.

Abstract

The fuel lance has a tip (21) with a nozzle surface having two fuel injectors (7). The nozzle surface is provided with slots (33) between the fuel nozzles. The nozzle surface is a ring surface, and the slots are run perpendicular to a peripheral direction of the ring surface by the slots.

Description

Die vorliegende Erfindung betrifft eine Brennerlanze, bspw. für einen Gasturbinenbrenner, und insbesondere eine Brennstofflanze für flüssige Brennstoffe.The present invention relates to a burner lance, for example for a gas turbine combustor, and more particularly to a fuel lance for liquid fuels.

Derartige Brennstofflanzen kommen beispielsweise bei Brennern zum Einsatz, die sowohl mit flüssigem Brennstoff, als auch mit gasförmigem Brennstoff betrieben werden können. In der Regel ist die Lanze zum Betrieb mit den flüssigen Brennstoffen, beispielsweise Öl, vorgesehen. Das Öl strömt dann durch die Lanze und tritt an ihrer Spitze durch Öldüsen in eine Brennkammer aus. Nach dem Austritt aus der Düse wird das Öl in der Brennkammer, in die auch Verdichterluft eingebracht wird, verbrannt. Gasförmige Brennstoffe werden dagegen häufig in einen die Düsenlanze umgebenden Luftzufuhrkanal eingedüst und dort mit Verdichterluft gemischt, bevor das Gemisch in die Brennkammer eingebracht wird.Such fuel lances are used for example in burners, which can be operated both with liquid fuel, as well as with gaseous fuel. In general, the lance for operation with the liquid fuels, such as oil, is provided. The oil then flows through the lance and exits at its tip through oil nozzles into a combustion chamber. After exiting the nozzle, the oil in the combustion chamber, in which compressor air is introduced, burned. In contrast, gaseous fuels are often injected into an air supply channel surrounding the nozzle lance and mixed there with compressor air before the mixture is introduced into the combustion chamber.

Beim Betrieb mit gasförmigen Brennstoffen ist die Lanzenspitze wegen der nahen Flamme in der Regel hohen Temperaturen im Bereich von bis zu ca. 1.000°C ausgesetzt. Diese hohen Temperaturen können zu einer Verkokung von Rückständen flüssiger Brennstoffe in der Düsenlanze führen. Vor einem Umschalten des Brenners auf einen Betrieb mit einem flüssigen Brennstoff erfolgt daher in der Regel eine Spülung der Brennstoffpassagen in der Brennstofflanze mit einem Kühlwasser, um eventuelle Ablagerungen wegzuspülen. Die Temperatur des Kühlwassers beträgt jedoch nur ca. 25°C, was zu einem Thermoschock in der heißen Brennstofflanze führen kann. Dabei bilden sich im Bereich der Düsen hohe Temperaturgradienten aus, so dass erhebliche Thermospannungen in der Lanzenspitze auftreten können. Durch das wiederholte Auftreten solcher Thermospannungen kann es zu Rissen im Bereich der Düsen kommen, wodurch die Startzahlen und somit die Lebensdauer der Brennstoffdüse verringert werden.When operated with gaseous fuels, the lance tip is usually exposed to high temperatures in the range of up to about 1000 ° C due to the near flame. These high temperatures can lead to coking of liquid fuel residues in the nozzle lance. Before switching the burner to operate with a liquid fuel is therefore usually a flushing of the fuel passages in the fuel lance with a cooling water to flush away any deposits. However, the temperature of the cooling water is only about 25 ° C, which can lead to a thermal shock in the hot fuel lance. In the process, high temperature gradients develop in the region of the nozzles, so that considerable thermoelectric voltages can occur in the lance tip. The repeated occurrence of such thermal stresses can lead to cracks in the area of the nozzles, as a result of which the starting numbers and thus the service life of the fuel nozzle are reduced.

Aufgabe der vorliegenden Erfindung ist es daher, eine Brennstofflanze für die Verwendung in einem Brenner, insbesondere in einem Gasturbinenbrenner, zur Verfügung zu stellen, welche die genannten Nachteile zu überwinden hilft. Eine weitere Aufgabe der Erfindung ist es, einen vorteilhaften Brennen, insbesondere einen Gasturbinenbrenner, zur Verfügung zu stellen.The object of the present invention is therefore to provide a fuel lance for use in a burner, in particular in a gas turbine burner, which helps to overcome the mentioned disadvantages. A further object of the invention is to provide an advantageous firing, in particular a gas turbine burner.

Die erste Aufgabe wird durch eine Brennstofflanze für einen Brenner, insbesondere für einen Gasturbinenbrenner, nach Anspruch 1 gelöst, die zweite Aufgabe durch einen Brenner, insbesondere einen Gasturbinenbrenner nach Anspruch 8. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.The first object is achieved by a fuel lance for a burner, in particular for a gas turbine burner, according to claim 1, the second object by a burner, in particular a gas turbine burner according to claim 8. The dependent claims contain advantageous embodiments of the invention.

Eine Brennerstofflanze für einen Brenner, insbesondere für einen Gasturbinenbrenner, umfasst eine Spitze, welche eine Düsenfläche mit wenigstens zwei Brennstoffdüsen aufweist. Die Düsenfläche ist zwischen den Brennstoffdüsen mit Schlitzen versehen. Sie kann insbesondere als Ringfläche ausgebildet sein, etwa als konische Ringfläche, wobei die Schlitze senkrecht zur Umfangsrichtung der Ringfläche durch diese verlaufen.A burner lance for a burner, in particular for a gas turbine burner, comprises a tip which has a nozzle surface with at least two fuel nozzles. The nozzle surface is slotted between the fuel nozzles. It may in particular be formed as an annular surface, such as a conical annular surface, wherein the slots extend perpendicular to the circumferential direction of the annular surface through this.

Die Schlitze in der Düsenfläche erlauben der Lanzenspitze das Abbauen thermischer Spannungen durch freie Verformung, so das thermische Gradienten die Brennstofflanze weniger belasten. Die Schlitze haben keinen wesentlichen aerodynamischen Einfluss auf die an der Brennstofflanze entlang strömende Luft oder auf Brennstoff, der durch die Brennstoffdüsen in den Luftstrom eingedüst wird. Die Schlitze bedeuten auch lediglich eine geringfügige Modifikation der Brennstofflanze, die zudem mit sehr geringem Aufwand vorgenommen werden kann. Daher können bestehende Brennstofflanzen mit geringem Aufwand nachgerüstet werden, wodurch sich die möglichen Startzahlen und die Lebensdauer dieser Brennstofflanze erhöhen.The slits in the nozzle surface allow the lance tip to dissipate thermal stresses through free deformation, thus reducing the thermal gradient of the fuel lance. The slots have no significant aerodynamic influence on the air flowing along the fuel lance or on fuel injected through the fuel nozzles into the airflow. The slots also mean only a minor modification of the fuel lance, which can also be made with very little effort. Therefore, existing fuel lances can be retrofitted with little effort, which increases the possible starting numbers and the life of this fuel lance.

In der Spitze können Kühlluftkanäle vorhanden sein, die zwischen den Brennstoffdüsen unterhalb der Düsenfläche verlaufen. Beispielsweise mittels durch die Kühlfluidkanäle hindurchgeleiteter Verdichterluft kann die Spitze der Brennstofflanze während des Betriebs des Brenners gekühlt werden, um die Temperatur der Spitze so gering wie möglich zu halten, und so das Auftreten von Thermospannungen während des Spülens der Brennstofflanze weiter zu vermindern. Die Schlitze reichen dann idealerweise von der Düsenfläche bis zu dem jeweiligem Kühlfluidkanal. Mit anderen Worten, die Schlitze bilden Durchgangsöffnungen von der Düsenfläche bis zum Kühlfluidkanal. Diese Ausgestaltung erlaubt eine besonderes hohe Flexibilität der entsprechenden Materialbereiche zum Abbau von Thermospannungen.In the tip cooling air channels may be present, which extend between the fuel nozzles below the nozzle surface. For example, by means of compressor air passing through the cooling fluid passages, the tip of the fuel lance may be cooled during operation of the burner to minimize the temperature of the tip, thereby further reducing the incidence of thermal stress during purging of the fuel lance. The slots then ideally extend from the nozzle surface to the respective cooling fluid channel. In other words, the slots form passage openings from the nozzle surface to the cooling fluid channel. This embodiment allows a particularly high flexibility of the corresponding material areas for the reduction of thermal voltages.

Wenn die Ringfläche eine konische Ringfläche ist, kann die Spitze der Brennstofflanze die Form eines Kegelstumpfes besitzen. In diesem Fall bildet die Mantelfläche des Kegelstumpfes die Düsenfläche, und die Kühlfluidkanäle weisen zumindest zur Deckfläche des Kegelstumpfes hin offene Austrittöffnungen auf. Alternativ oder zusätzlich zu den erwähnten Austrittsöffnungen können um die Brennstoffdüsen herum Durchgangsöffnungen vorhanden sein, die mit den Luftzufuhrkanälen in strömungstechnischer Verbindung stehen. Durch diese Öffnungen austretende Verdichterluft kann dann dazu Verwendung finden, die Spitze der Lanze insbesondere im Bereich der zu spulenden Düsen zu kühlen. Beim Vorhandensein solcher Durchgangsöffnungen kann zwischen den Durchgangsöffnungen benachbarter Brennstoffdüsen insbesondere jeweils ein Schlitz angeordnet sein.If the annular surface is a conical annular surface, the tip of the fuel lance may be in the shape of a truncated cone. In this case, the lateral surface of the truncated cone forms the nozzle surface, and the cooling fluid channels have at least open outlet openings towards the top surface of the truncated cone. As an alternative or in addition to the aforementioned outlet openings, passage openings may be present around the fuel nozzles which are in fluid communication with the air supply channels. Compressor air exiting through these openings can then be used to cool the tip of the lance, in particular in the region of the nozzles to be spooled. In the presence of such passage openings, in particular a respective slot can be arranged in each case between the passage openings of adjacent fuel nozzles.

Ein erfindungsgemäßer Brenner, der insbesondere ein Gasturbinenbrenner sein kann, ist mit einer erfindungsgemäßen Brennstofflanze ausgestattet. Die Brennstofflanze kann hierbei zur Zufuhr eines flüssigen Brennstoffes Verwendung finden, wobei zusätzlich zur Brennstofflanze Brennstoffdüsen für gasförmige Brennstoffe vorhanden sein können.A burner according to the invention, which may in particular be a gas turbine burner, is equipped with a fuel lance according to the invention. The fuel lance can be used here for supplying a liquid fuel, wherein in addition to the fuel lance fuel nozzles for gaseous fuels can be present.

Die Verwendung der erfindungsgemäßen Brennstofflanze im erfindungsgemäßen Brenner führt aufgrund der erhöhten Lebensdauer der Brennstofflanze dazu, dass die Wartungsintervalle für einen solchen Brenner verlängert werden können, was die Betriebskosten senkt.The use of the fuel lance according to the invention in the burner according to the invention leads to the fact that the maintenance intervals for such a burner can be extended due to the increased service life of the fuel lance, which reduces the operating costs.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung eines Ausführungsbeispiels unter Bezugnahme auf die beiliegenden Figuren.Further features, properties and advantages of the present invention will become apparent from the following description of an embodiment with reference to the accompanying figures.

Fig. 1 zeigt einen Ausschnitt aus einem erfindungsgemäßen Brenner in einer geschnittenen Darstellung. Fig. 1 shows a section of a burner according to the invention in a sectional view.

Fig. 2 zeigt die Spitze der Düsenlanze des erfindungsgemäßen Brenners in Fig. 1 in einer perspektivischen Darstellung. Fig. 2 shows the tip of the nozzle lance of the burner according to the invention in Fig. 1 in a perspective view.

Fig. 3 zeigt die Spitze aus Fig. 2 in einer Ansicht auf ihre Vorderseite. Fig. 3 shows the tip Fig. 2 in a view on her front.

Als ein Ausführungsbeispiel für einen erfindungsgemäßen Brenner ist in Fig. 1 ein Gasturbinenbrenner dargestellt. Dieser weist einen von einer im Wesentlichen zylinderförmigen Wand 1 begrenzten Luftzufuhrkanal 3 auf, in dessen Zentrum eine Brennstofflanze 5 verläuft. An der Spitze der Brennstofflanze sind Brennstoffdüsen 7 zum Eindüsen eines Brennstoffes in die durch den Luftzufuhrkanal 3 zugeführte Luft vorhanden. Im vorliegenden Ausführungsbeispiel ist die Brennstofflanze 5 eine Öllanze zum Zuführen eines flüssigen Brennstoffes.As an embodiment of a burner according to the invention is in Fig. 1 a gas turbine burner shown. This has one of a substantially cylindrical wall 1 bounded air supply channel 3, in the center of a fuel lance 5 extends. At the tip of the fuel lance are fuel nozzles 7 for injecting a fuel into the air supplied through the air supply passage 3. In the present embodiment, the fuel lance 5 is an oil lance for supplying a liquid fuel.

Neben der Brennstofflanze umfasst der Brenner ein zweites Brennstoffzufuhrsystem 9, welches eine axiale Durchführung 11 besitzt, durch die die Brennstofflanze 5 hindurchgeführt ist, so dass lediglich der Endabschnitt 13 der Brennstofflanze 5 aus dem Brennstoffzufuhrsystem 9 herausragt. Das Brennstoffzufuhrsystem 9 ist mit Drallschaufeln 15 verbunden, die sich am abströmseitigen Ende des Brennstoffzufuhrsystems 9 befinden und sich durch den Luftzufuhrkanal 3 erstrecken. Mittels Brennstoffzufuhrkanälen 17 wird ein Brennstoff, im vorliegenden Ausführungsbeispiel ein gasförmiger Brennstoff, in die Drallschaufeln 15 geleitet, von wo er durch Düsenöffnungen 19 in die durch den Luftzufuhrkanal 3 strömende Luft eingedüst wird.In addition to the fuel lance burner includes a second fuel supply system 9, which has an axial passage 11 through which the fuel lance 5 is passed, so that only the end portion 13 of the fuel lance 5 protrudes from the fuel supply system 9. The fuel supply system 9 is connected to swirl vanes 15 located at the downstream end of the fuel supply system 9 and extending through the air supply passage 3. through Fuel supply channels 17, a fuel, in the present embodiment, a gaseous fuel, passed into the swirl vanes 15, from where it is injected through nozzle openings 19 in the air flowing through the air supply duct 3 air.

Bei dem in Fig. 1 dargestellten Brenner handelt es sich um einen sogenannten "Dual Fuel Brenners", also einen Brenner, der sowohl mit gasförmigen Brennstoffen, als auch mit flüssigen Brennstoffen betrieben werden kann. Die Erfindung kann jedoch auch im Rahmen von Brennern realisiert werden, in denen sowohl durch das Brennstoffzufuhrsystem, als auch durch die Brennstofflanze jeweils ein Brennstoff im selben Aggregatzustand zugeführt wird, also beispielsweise im Rahmen eines Brenners, in dem sowohl durch das Brennstoffzufuhrsystem, als auch durch die Brennstofflanze jeweils ein gasförmiger Brennstoff zugeführt wird. Beispielsweise kann dann die Brennstofflanze als Pilotbrenner Verwendung finden.At the in Fig. 1 The burner shown is a so-called "dual fuel burner", so a burner that can be operated with both gaseous fuels, as well as with liquid fuels. However, the invention can also be implemented in the context of burners in which both the fuel supply system, and by the fuel lance each a fuel in the same state of matter is supplied, so for example in the context of a burner in which both by the fuel supply system, and by the fuel lance in each case a gaseous fuel is supplied. For example, then the fuel lance can be used as a pilot burner.

Eine perspektivische Darstellung des Endabschnittes 13 der Brennstofflanze 5 ist in Fig. 2 gezeigt. Fig. 3 zeigt außerdem eine Frontalansicht auf den Endabschnitt in Blickrichtung entlang der Axialrichtung der Brennstofflanze 5.A perspective view of the end portion 13 of the fuel lance 5 is shown in FIG Fig. 2 shown. Fig. 3 also shows a frontal view of the end portion in the direction along the axial direction of the fuel lance 5.

Mit Bezug auf die Fig. 1 bis 3 wird nun nachfolgend die Endabschnitt 13 näher beschrieben. Der Endabschnitt 13 umfasst einen im Wesentlichen zylindrischen Abschnitt 20, an dem sich eine im Wesentlichen kegelstumpfförmige Spitze 21 anschließt. In der Mantelfläche 23 der kegelstumpfförmigen Spitze 21 sind drei Brennstoffdüsen 7 in Umfangsrichtung gleichmäßig verteilt angeordnet, wie insbesondere Fig. 3 erkennen lässt. Es sei an dieser Stelle aber darauf hingewiesen, dass eine Spitze mit drei Brennstoffdüsen lediglich eine mögliche Ausführungsvariante darstellt und dass mehr oder weniger Brennstoffdüsen oder eine andere Verteilung der Düsen in der Mantelfläche möglich sind.With reference to the Fig. 1 to 3 Now, the end portion 13 will be described in more detail below. The end portion 13 comprises a substantially cylindrical portion 20, followed by a substantially frusto-conical tip 21 connects. In the lateral surface 23 of the frusto-conical tip 21, three fuel nozzles 7 are distributed uniformly in the circumferential direction, in particular Fig. 3 lets recognize. It should be noted at this point, however, that a tip with three fuel nozzles represents only one possible embodiment variant and that more or fewer fuel nozzles or a different distribution of the nozzles in the lateral surface are possible.

Zum Kühlen der Spitze 21 ist diese mit Kühlluftkanälen 25 versehen, die in eine zentrale Öffnung 27 münden. Diese befindet sich dort, wo die Deckfläche des Kegelstumpfes verläuft. Gespeist werden die Kühlluftkanäle 25 durch Speiseöffnungen 29 im zylinderförmigen Abschnitt 20 des Endabschnittes 13 der Düsenlanze 5. Beim Betrieb des Brenners strömt ein Teil der durch den Luftzufuhrkanal 3 einströmenden Luft durch die Speiseöffnungen 29 in die Kühlluftkanäle 25. Diese Luft weist Temperaturen auf, die kühler sind, als die Temperatur der Spitze 21. Dennoch wird die Spitze 21 beim Gasbetrieb des dargestellten Brenners durch die im Flammenraum vorherrschende Flamme auf Temperaturen von rund 800 bis 1.000°C aufgeheizt.For cooling the tip 21, this is provided with cooling air channels 25, which open into a central opening 27. This is located where the top surface of the truncated cone runs. The cooling air channels 25 are fed through feed openings 29 in the cylindrical portion 20 of the end portion 13 of the nozzle lance 5. During operation of the burner flows part of the air flowing through the air supply passage 3 through the feed openings 29 in the cooling air channels 25. This air has temperatures that are cooler However, the tip 21 is heated in the gas operation of the illustrated burner by the prevailing flame in the flame chamber to temperatures of about 800 to 1,000 ° C.

Wenn vom Gasbetrieb, bei dem der gasförmige Brennstoff durch das Brennstoffzufuhrsystem 9 zugeführt wird, auf den Ölbetrieb umgestellt werden soll, in dem der Brennstoff durch die Brennstofflanze zugeführt wird, erfolgt eine Spülung der Brennstoffpassage 31 und der Brennstoffdüsen 7 der Brennstofflanze 5, um Verkokungen zu vermeiden. Dieses Spülen wird typischerweise mit Wasser durchgeführt, welches eine Temperatur von etwa 25°C besitzt. Aufgrund der hohen Temperaturdifferenz zwischen dem Spülwasser einerseits und der Spitze 21 andererseits kommt es hierbei in der Spitze zu Thermospannungen, die definiert abzubauen sind. Um das definierte Abbauen dieser Thermospannungen zu ermöglichen, ist die die Düsenfläche bildende Mantelfläche 23 der Spitze 21 mit Schlitzen 33 versehen. Die Schlitze 33 erstrecken sich im vorliegenden Ausführungsbeispiel durch die Mantelfläche 23 hindurch bis zu den Kühlluftkanälen 25, so dass beim Betrieb des Brenners Kühlluft durch die Schlitze 33 austreten kann, um diese gegen den Eintritt von heißen Verbrennungsgasen zu sperren.When switching from the gas operation in which the gaseous fuel is supplied through the fuel supply system 9 to the oil operation in which the fuel is supplied through the fuel lance, the fuel passage 31 and the fuel nozzles 7 of the fuel lance 5 are purged to allow coking avoid. This rinsing is typically carried out with water having a temperature of about 25 ° C. Due to the high temperature difference between the rinsing water on the one hand and the tip 21 on the other hand, it comes here in the peak to thermal stresses that are defined breakdown. In order to allow the defined reduction of these thermal stresses, the nozzle surface forming lateral surface 23 of the tip 21 is provided with slots 33. The slots 33 extend in the present embodiment through the lateral surface 23 through to the cooling air passages 25, so that during operation of the burner cooling air can escape through the slots 33 to lock them against the entry of hot combustion gases.

Im vorliegenden Ausführungsbeispiel reichen die Schlitze 33 zudem bis zu den Speiseöffnungen 29. Sie können jedoch auch lediglich in der Mantelfläche 23 des Kegelstumpfes angeordnet sein, so dass kein Schlitzabschnitt durch den zylinderförmigen Abschnitt 20 verläuft.In the present embodiment, the slots 33 also extend to the feed openings 29. However, they can also be arranged only in the lateral surface 23 of the truncated cone, so that no slot section extends through the cylindrical portion 20.

Die Schlitze 33 sind im vorliegenden Ausführungsbeispiel jeweils in der Mitte zwischen zwei Brennstoffdüsen 7 angeordnet. In Abhängigkeit von den strömungstechnischen Gegebenheiten im Bereich der Spitze (beispielsweise unter Berücksichtigung des von den Drallerzeugern 15 erzeugten Dralls) können die Schlitze 33 jedoch auch im Vergleich zudem in den Fig. dargestellten Ausführungsbeispiel im Uhrzeigersinn oder entgegen dem Uhrzeigersinn versetzt sein. Außerdem ist es möglich, mehrere Schlitze vorzusehen, wenn diese sich nur durch die Mantelfläche 23 des Kegelstumpfes 21, nicht aber durch den zylinderförmigen Abschnitt 20 erstrecken. Die durch die Schlitze 33 möglich werdende Verformung der Kegelstumpfmantelfläche 23 im Bereich der Kühlluftkanäle 25 ermöglicht dann das Abbauen der während des Spülprozesses auftretenden Thermospannungen.The slots 33 are each arranged in the middle between two fuel nozzles 7 in the present embodiment. Depending on the fluidic conditions in the region of the tip (for example, taking into account the twist generated by the swirl generators 15), however, the slots 33 can also be offset in the clockwise or counterclockwise direction in comparison with the embodiment shown in the FIG. In addition, it is possible to provide a plurality of slots if they extend only through the lateral surface 23 of the truncated cone 21, but not through the cylindrical portion 20. The possible through the slots 33 deformation of the truncated cone surface 23 in the region of the cooling air channels 25 then allows the degradation of the thermal stresses occurring during the rinsing process.

Im vorliegenden Ausführungsbeispiel sind um die Brennstoffdüsen 7 herum außerdem optionale Durchgangsbohrungen 30 vorhanden, die bis zu den Kühlluftkanälen 25 reichen und die den Durchtritt von Kühlfluid ermöglichen. Hierdurch lässt sich eine besonders effektive Kühlung des Materials der Lanzenspitze im Bereich der zu spulenden Düsenöffnungen 7 erreichen, wodurch der Thermoschock beim Spülen und somit auch die abzubauenden Thermospannungen verringert werden.In the present embodiment, also around the fuel nozzles 7 optional through holes 30 are present, which extend to the cooling air passages 25 and allow the passage of cooling fluid. In this way, a particularly effective cooling of the material of the lance tip in the region of the nozzle openings to be reeled 7 can be achieved, whereby the thermal shock during flushing and thus the degraded thermoelectric voltages are reduced.

Das Vorsehen der Schlitze 33 in der Brennstofflanze des erfindungsgemäßen Brenners ermöglicht in vorteilhafter Weise den Abbau von Thermospannungen während des Spülens der Brennstofflanze mit Spülwasser, ohne dass die Schlitze die Aerodynamik im Bereich der Spitze der Brennstofflanze negativ beeinflussen. Durch den verbesserten Abbau der Thermospannungen wird die Lebensdauer der Brennstofflanze verlängert. Das Einbringen der Schlitze in bestehende Brennstofflanzen ohne Schlitze ist zudem ohne großen Aufwand realisierbar, so dass bereits existierende Brennstofflanzen mit geringem Aufwand umgerüstet werden können.The provision of the slots 33 in the fuel lance of the burner according to the invention advantageously allows the removal of thermal stresses during flushing of the fuel lance with rinse water, without the slots adversely affect the aerodynamics in the tip of the fuel lance. Due to the improved reduction of the thermal voltages, the life of the fuel lance is extended. The introduction of the slots in existing fuel lances without slots is also feasible without much effort, so that existing fuel lances can be converted with little effort.

Claims (9)

Brennstofflanze (5) für einen Brenner, insbesondre für einen Gasturbinenbrenner, mit einer Spitze (21), welche eine Düsenfläche (23) mit wenigstens zwei Brennstoffdüsen (7) aufweist, wobei die Düsenfläche zwischen den Brennstoffdüsen mit Schlitzen (33) versehen ist.A fuel lance (5) for a burner, in particular for a gas turbine burner, having a tip (21) having a nozzle surface (23) with at least two fuel nozzles (7), the nozzle surface being provided with slots (33) between the fuel nozzles. Brennstofflanze (5) nach Anspruch 1, in der die Düsenfläche eine Ringfläche (23) ist und die Schlitze (33) senkrecht zur Umfangsrichtung der Ringfläche (23) durch diese verlaufen.A fuel lance (5) according to claim 1, wherein the nozzle surface is an annular surface (23) and the slots (33) are perpendicular to the circumferential direction of the annular surface (23). Brennstofflanze nach Anspruch 2, in der die Ringfläche eine konische Ringfläche (23) ist.A fuel lance according to claim 2, wherein the annular surface is a conical annular surface (23). Brennstofflanze nach einem der Ansprüche 1 bis 3, in der in der Spitze (21) Kühlluftkanäle (25) vorhanden sind, die zwischen den Brennstoffdüsen (7) unterhalb der Düsenfläche (23) verlaufen, wobei die Schlitze (33) von der Düsenfläche (23) bis zu dem jeweiligen Kühlluftkanal (25) reichen.A fuel lance according to any one of claims 1 to 3, wherein there are cooling air passages (25) in the tip (21) extending between the fuel nozzles (7) below the nozzle surface (23), the slots (33) being spaced from the nozzle surface (23 ) to reach the respective cooling air duct (25). Brennstofflanze nach Anspruch 3 und Anspruch 4, in der die Spitze (21) die Form eines Kegelstumpfes besitzt, die Mantelfläche (23) des Kegelstumpfes die Düsenfläche bildet und die Kühlluftkanäle (25) zumindest zur Deckfläche des Kegelstumpfes hin Öffnungen (27) aufweisen.Fuel lance according to claim 3 and claim 4, in which the tip (21) has the shape of a truncated cone, the lateral surface (23) of the truncated cone forms the nozzle surface and the cooling air channels (25) have openings (27) at least towards the top surface of the truncated cone. Brennstofflanze nach Anspruch 4 oder Anspruch 5, in der um die Brennstoffdüsen (7) herum Durchgangsöffnungen (30) vorhanden sind, die mit den Luftzufuhrkanälen (25) in strömungstechnischer Verbindung stehen.A fuel lance according to claim 4 or claim 5, wherein passage openings (30) are provided around the fuel nozzles (7) in fluid communication with the air supply passages (25). Brennstofflanze nach Anspruch 6, in der zwischen den Durchgangsöffnungen (30) benachbarter Brennstoffdüsen (7) jeweils ein Schlitz (33) angeordnet ist.Fuel lance according to Claim 6, in which a slot (33) is arranged in each case between the passage openings (30) of adjacent fuel nozzles (7). Brenner, insbesondere Gasturbinenbrenner, mit einer Brennstofflanze (5) nach einem der vorangehenden Ansprüche.Burner, in particular gas turbine burner, with a fuel lance (5) according to one of the preceding claims. Brenner nach Anspruch 8, in welchem die Brennstofflanze (5) zur Zufuhr eines flüssigen Brennstoffes Verwendung findet und welcher zusätzlich zur Brennstofflanze (5) Brennstoffdüsen (19) für gasförmige Brennstoffe aufweist.Burner according to Claim 8, in which the fuel lance (5) is used to supply a liquid fuel and which has fuel nozzles (19) for gaseous fuels in addition to the fuel lance (5).
EP08171548A 2008-12-12 2008-12-12 Fuel lance for a burner Withdrawn EP2196734A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP08171548A EP2196734A1 (en) 2008-12-12 2008-12-12 Fuel lance for a burner
PCT/EP2009/064664 WO2010066516A2 (en) 2008-12-12 2009-11-05 Fuel lance for a burner
JP2011539985A JP5340410B2 (en) 2008-12-12 2009-11-05 Burner fuel lance
US13/133,741 US8973367B2 (en) 2008-12-12 2009-11-05 Fuel lance for A burner
RU2011128704/06A RU2529970C2 (en) 2008-12-12 2009-11-05 Fuel tube for burner
EP09752330A EP2359065A2 (en) 2008-12-12 2009-11-05 Fuel lance for a burner
CN200980149749.XA CN102265091B (en) 2008-12-12 2009-11-05 Fuel lance for burner

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EP08171548A EP2196734A1 (en) 2008-12-12 2008-12-12 Fuel lance for a burner

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EP2196734A1 true EP2196734A1 (en) 2010-06-16

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EP09752330A Withdrawn EP2359065A2 (en) 2008-12-12 2009-11-05 Fuel lance for a burner

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RU2529970C2 (en) 2014-10-10
US8973367B2 (en) 2015-03-10
WO2010066516A3 (en) 2011-04-21
EP2359065A2 (en) 2011-08-24
JP2012511687A (en) 2012-05-24
US20110247338A1 (en) 2011-10-13
RU2011128704A (en) 2013-01-20
JP5340410B2 (en) 2013-11-13
CN102265091A (en) 2011-11-30
WO2010066516A2 (en) 2010-06-17

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