EP2507557B1 - Burner assembly - Google Patents

Burner assembly Download PDF

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Publication number
EP2507557B1
EP2507557B1 EP10779300.2A EP10779300A EP2507557B1 EP 2507557 B1 EP2507557 B1 EP 2507557B1 EP 10779300 A EP10779300 A EP 10779300A EP 2507557 B1 EP2507557 B1 EP 2507557B1
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EP
European Patent Office
Prior art keywords
fuel
burner assembly
assembly according
distribution ring
slot
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.)
Not-in-force
Application number
EP10779300.2A
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German (de)
French (fr)
Other versions
EP2507557A1 (en
Inventor
Andreas Böttcher
Tobias Krieger
Daniel Vogtmann
Ulrich Wörz
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Siemens AG
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Siemens AG
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Priority to EP10779300.2A priority Critical patent/EP2507557B1/en
Publication of EP2507557A1 publication Critical patent/EP2507557A1/en
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Publication of EP2507557B1 publication Critical patent/EP2507557B1/en
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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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23D2211/00—Thermal dilatation prevention or compensation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components

Definitions

  • the present invention relates to a burner assembly and more particularly to a burner assembly for gas turbines.
  • a gas turbine comprises as essential components a compressor, a turbine with moving blades and at least one combustion chamber.
  • the blades of the turbine are arranged as blade rings on a shaft extending mostly through the entire gas turbine, which is coupled to a consumer, such as a generator for power generation.
  • the shaft provided with the blades is also called turbine runner or rotor. Between the blade rings are vanes, which serve as nozzles for guiding the working fluid through the turbine.
  • the combustion chamber is supplied with compressed air from the compressor.
  • the compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber.
  • the hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.
  • the vanes serve to optimize the momentum transfer.
  • a typical burner assembly for gas turbines as shown in US 6,082,111 is described and how it is used in particular in so-called tube combustion chambers, usually has an annular support with uniformly distributed around the circumference of the ring nozzle lances.
  • fuel nozzle openings are arranged, with which fuel can be injected into an air supply channel.
  • the fuel nozzles represent a main stage of the burner, which is used to generate a premix flame, ie a flame, in which the air and the fuel mix before igniting become, serve.
  • premix burners are operated with lean air-fuel mixtures, that is, with mixtures containing relatively little fuel.
  • pilot burner Through the center of the annular fuel distributor ring typically extends a pilot burner, which is designed as a diffusion burner, i. it produces a flame in which the fuel is injected directly into the flame without first being mixed with air.
  • the pilot burner in addition to starting the gas turbine, also serves to stabilize the premix flame which, to minimize emissions, is often operated in a range of air to fuel mixing ratio which could lead to flame instabilities without assistive pilot flame.
  • the fuel distributor ring is characterized by a short service life.
  • the burner arrangement comprises a fuel distributor ring ring and a number of fuel nozzles which are mounted in the flow direction to the fuel distributor ring.
  • the fuel distributor ring has an annular surface in the flow direction.
  • the fuel distributor ring an outer side facing the middle of the ring and an opposite outer side.
  • At least one slot is now present on the surface between the fuel nozzles. Through this discharge slot results in a better heat distribution in the material of the fuel distributor, whereby the voltages are reduced and sets a longer life expectancy.
  • the relief slot can vary in depth, width and length and be adapted to the respective Brennstoffverteilerring.
  • the at least one slot extends on the surface from the outside to the inside. Thus, stress relief is provided over a wide surface area.
  • At least one recess is arranged on the surface. Due to the at least one recess, especially in connection with the slots, an optimized geometry results, which results in a better heat distribution in the material of the fuel distributor ring. Due to the better heat distribution no locally excessive voltages occur and the required service life cycles can be achieved. The voltage can thus be reduced in this range from originally over 950MPa to 600MPa.
  • the at least one recess also partially includes the outside of the fuel distributor ring.
  • the at least one recess is substantially round.
  • a plurality of fuel nozzles are present, wherein between each adjacent fuel nozzle, a slot is present.
  • the entire surface ring of the fuel distributor ring is coated with relief slots.
  • the at least one slot is substantially Y-shaped.
  • the at least one Y-shaped slot comprises two arms and one leg, wherein the two arms of the substantially Y-shaped slot point to the outside of the fuel distributor ring.
  • the two arms of the substantially y-shaped slot may also point to the inside of the fuel distributor ring.
  • the at least one recess may have a radius, wherein the radius decreases seen in the flow direction.
  • the fuel distributor ring preferably comprises at least one nickel alloy, in particular a nickel-molybdenum alloy, or a nickel-chromium-iron-molybdenum alloy. These alloys are particularly resistant to high temperatures.
  • the fuel distributor ring comprises in its interior at least two fuel channels for two combustion stages A and B.
  • the two fuel channels comprise two supply connections.
  • the fuel nozzles can be supplied separately and separately depending on the load state of the engine fuels.
  • 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 ring 27, eight fuel nozzles 29 extending from the fuel distributor ring 27 and eight swirlers 31 arranged in the region of the tips of the fuel nozzles 29.
  • the fuel distributor ring 27 and the fuel nozzles 29 together form a burner housing through which fuel lines extend to Eindüsö réelleen disposed within the swirl generator 31.
  • the fuel nozzles 29 may be welded to the fuel distributor ring 27.
  • the burner can be connected to fuel supply lines.
  • 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 29 may be greater than or less than eight, for example, six fuel nozzles 29 or twelve fuel nozzles 29 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.
  • the fuel distributor ring 27 has the task of distributing the fuel to the fuel nozzles 29. It is internally provided with two fuel channels 41, 42 each of which supplies a number of nozzles 29 (4 nozzles 29 in this particular case) with fuel as a stage A and a stage B ( FIG. 3 and FIG. 4 ).
  • the two fuel passages 41 and 42 include two supply ports 51, 52 for supplying fuel. These can also be different types of fuel.
  • the fuel distributor ring 27 flows from the outside with up to 500 ° C warm compressor air, but from the inside with cold fuel, which in extreme cases can only have a temperature of 20 ° C. As a result, very high voltages occur at the fuel distributor ring 27. Especially on the nozzles 29 facing surface side 54 of the fuel distributor ring 27 occur very high voltages, so that the life can not be achieved.
  • the fuel distributor ring 27 has an annular surface 54 in the flow direction and an outer inner side 56 pointing to the middle of the ring and an outer outer side 58 opposite to it.
  • At least one slot 60 is now present on the surface 54 between the fuel nozzles 29.
  • This is essentially y-shaped ( FIG. 3 and FIG. 5 ).
  • substantially Y-shaped means that all forms are here encompassed which approximately remind one of the letter Y, that is to say have two arms 62 and one leg 63.
  • all spaces on the surface 54 between the nozzles 29 are provided with such slots 60.
  • the slot 60, and in particular the y-shaped slot 60 extends on the surface 54 from the outside 58 to the inside 56.
  • the two arms 62 of the substantially Y-shaped slot 60 can advantageously be arranged on the outside 58 of the surface 54 of the fuel distributor ring 27.
  • recesses 66 are arranged on the surface 54 (FIG. FIG. 5 ). These recesses 66 are arranged on the surface 54 such that they partially also include the outside 58 of the fuel distributor ring 27, that is, there is a recess from the outside 58 of the fuel distributor 27.
  • the recess 66 may vary in depth and shape. However, this is preferably a substantially circular recess 66.
  • the recesses 66 may have a radius and the radius seen in the flow direction decrease. This makes it even more effective to avoid the high thermal gradient during operation and the resulting stresses.
  • the fuel distributor ring 27 preferably comprises at least one nickel alloy, in particular a nickel-molybdenum alloy. This material is particularly heat-resistant and therefore particularly suitable for burners.
  • the burner assembly according to the invention can be used in particular in a gas turbine.
  • slots 60 and recesses 66 according to the invention can be built into existing fuel distributor rings 27 in terms of production technology, since they do not require any far-reaching conversions and are therefore easy to implement in terms of manufacturing technology. Even on the previous aero performance of the burner creates only minimal impact.

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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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Description

Die vorliegende Erfindung betrifft eine Brenneranordnung und insbesondere eine Brenneranordnung für Gasturbinen.The present invention relates to a burner assembly and more particularly to a burner assembly for gas turbines.

Eine Gasturbine umfasst als wesentliche Bestandteile einen Verdichter, eine Turbine mit Laufschaufeln sowie wenigstens eine Brennkammer. Die Laufschaufeln der Turbine sind als Laufschaufelkränze an einer sich zumeist durch die gesamte Gasturbine erstreckende Welle angeordnet, die mit einem Verbraucher, etwa einem Generator zur Stromerzeugung, gekoppelt ist. Die mit den Laufschaufeln versehene Welle wird auch Turbinenläufer oder Rotor genannt. Zwischen den Laufschaufelkränzen befinden sich Leitschaufelkränze, die als Düsen zum Leiten des Arbeitsmediums durch die Turbine dienen.A gas turbine comprises as essential components a compressor, a turbine with moving blades and at least one combustion chamber. The blades of the turbine are arranged as blade rings on a shaft extending mostly through the entire gas turbine, which is coupled to a consumer, such as a generator for power generation. The shaft provided with the blades is also called turbine runner or rotor. Between the blade rings are vanes, which serve as nozzles for guiding the working fluid through the turbine.

Im Betrieb der Gasturbine wird der Brennkammer verdichtete Luft aus dem Verdichter zugeführt. Die verdichtete Luft wird mit einem Brennstoff, beispielsweise Öl oder Gas, vermischt und das Gemisch in der Brennkammer verbrannt. Die heißen Verbrennungsabgase werden schließlich als Arbeitsmedium über einen Brennkammerausgang der Turbine zugeführt, wo sie unter Entspannung und Abkühlung Impuls auf die Laufschaufeln übertragen und so Arbeit leisten. Die Leitschaufeln dienen dabei zum Optimieren des Impulsübertrags.During operation of the gas turbine, the combustion chamber is supplied with compressed air from the compressor. The compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber. The hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work. The vanes serve to optimize the momentum transfer.

Eine typische Brenneranordnung für Gasturbinen, wie sie in US 6,082,111 beschrieben ist und wie sie insbesondere bei sogenannten Rohrbrennkammern zur Anwendung kommt, weist in der Regel einen ringförmigen Träger mit um den Umfang des Ringes gleichmäßig verteilten Düsenlanzen auf. In diesen Düsenlanzen sind Brennstoffdüsenöffnungen angeordnet, mit denen Brennstoff in einen Luftzufuhrkanal eingedüst werden kann. Die Brennstoffdüsen stellen eine Hauptstufe des Brenners dar, die zum Erzeugen einer Vormischflamme, also einer Flamme, bei welcher die Luft und der Brennstoff vor dem Zünden vermischt werden, dient. Um die NOx-Bildung in der Flamme zu minimieren werden, Vormischbrenner mit mageren Luft-Brennstoff-Gemischen, also mit Gemischen, die verhältnismäßig wenig Brennstoff enthalten, betrieben.A typical burner assembly for gas turbines, as shown in US 6,082,111 is described and how it is used in particular in so-called tube combustion chambers, usually has an annular support with uniformly distributed around the circumference of the ring nozzle lances. In these nozzle lances fuel nozzle openings are arranged, with which fuel can be injected into an air supply channel. The fuel nozzles represent a main stage of the burner, which is used to generate a premix flame, ie a flame, in which the air and the fuel mix before igniting become, serve. In order to minimize NO x formation in the flame, premix burners are operated with lean air-fuel mixtures, that is, with mixtures containing relatively little fuel.

Durch das Zentrum des ringförmigen Brennstoffverteilerrings erstreckt sich typischerweise ein Pilotbrenner, der als Diffusionsbrenner ausgebildet ist, d.h. er erzeugt eine Flamme, bei welcher der Brennstoff direkt in die Flamme eingedüst wird, ohne vorher mit Luft vermischt zu werden. Der Pilotbrenner dient außer zum Anfahren der Gasturbine auch zum Stabilisieren der Vormischflamme, die zum Minimieren des Schadstoffausstoßes häufig in einem Bereich des Mischungsverhältnisses von Luft zu Brennstoff betrieben wird, der ohne unterstützende Pilotflamme zu Flammeninstabilitäten führen könnte.Through the center of the annular fuel distributor ring typically extends a pilot burner, which is designed as a diffusion burner, i. it produces a flame in which the fuel is injected directly into the flame without first being mixed with air. The pilot burner, in addition to starting the gas turbine, also serves to stabilize the premix flame which, to minimize emissions, is often operated in a range of air to fuel mixing ratio which could lead to flame instabilities without assistive pilot flame.

Bei hohen Verbrennungstemperaturen zeichnet sich der Brennstoffverteilerring durch eine geringe Lebensdauer aus.At high combustion temperatures, the fuel distributor ring is characterized by a short service life.

Es ist daher eine Aufgabe der vorliegenden Erfindung, eine vorteilhafte Brenneranordnung mit einem Brennstoffverteilerring zur Verfügung zu stellen, welche eine besonders hohe Lebensdauer aufweist. Es ist eine weitere Aufgabe eine vorteilhafte Gasturbine mit einer solchen Brenneranordnung zur Verfügung zu stellen.It is therefore an object of the present invention to provide an advantageous burner arrangement with a fuel distributor ring which has a particularly long service life. It is a further object to provide an advantageous gas turbine with such a burner arrangement available.

Diese Aufgabe wird durch eine Brenneranordnung nach Anspruch 1 gelöst. Die auf die Gasturbine bezogene Aufgabe wird durch die Angabe einer Gasturbine nach Anspruch 12 gelöst. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.This object is achieved by a burner assembly according to claim 1. The object related to the gas turbine is solved by the specification of a gas turbine according to claim 12. The dependent claims contain advantageous embodiments of the invention.

Dabei umfasst die Brenneranordnung einen Brennstoffverteilerringring sowie eine Anzahl von Brennstoffdüsen welche in Strömungsrichtung an den Brennstoffverteilerring montiert sind. Der Brennstoffverteilerring weist in Strömungsrichtung eine ringförmige Oberfläche auf. Zudem weist der Brennstoffverteilerring eine zur Ringmitte weisende äußere Innenseite und eine gegenüberliegende äußere Außenseite auf.In this case, the burner arrangement comprises a fuel distributor ring ring and a number of fuel nozzles which are mounted in the flow direction to the fuel distributor ring. The fuel distributor ring has an annular surface in the flow direction. In addition, the fuel distributor ring an outer side facing the middle of the ring and an opposite outer side.

Da der Brennstoffverteilerring von außen, das heißt an den jeweiligen Außenseiten, jedoch mit bis zu 500°C warmer Verdichterendluft umströmt, aber im Innen mit kaltem Brennstoff durchströmt wird, der im Extremfall lediglich 20°C aufweist, wurde erkannt, dass dadurch am Brennstoffverteilerring hohe thermische Gradienten und damit verbunden sehr hohe Spannungen auftreten. Dadurch wird die Lebensdauer des Bauteils wesentlich beeinflusst. Insbesondere an der Oberfläche des Brennstoffverteilerrings treten hohe Spannungen auf.Since the fuel distributor ring from the outside, that is at the respective outer sides, but flows around with up to 500 ° C warm Verdichterendluft, but is traversed inside with cold fuel, which has only 20 ° C in extreme cases, it was recognized that thereby high fuel distributor ring thermal gradients and associated very high voltages occur. This significantly affects the life of the component. In particular, high voltages occur on the surface of the fuel distributor ring.

Erfindungsgemäß ist nun auf der Oberfläche zwischen den Brennstoffdüsen zumindest ein Schlitz vorhanden. Durch diesen Entlastungsschlitz ergibt sich eine bessere Wärmeverteilung in dem Werkstoff des Brennstoffverteilers, wodurch die Spannungen reduziert werden und sich eine höhere Lebenserwartung einstellt. Der Entlastungsschlitz kann dabei in Tiefe, Breite und Länge variieren und auf den jeweiligen Brennstoffverteilerring angepasst werden. Der zumindest eine Schlitz erstreckt sich auf der Oberfläche von der Außenseite bis zur Innenseite. Somit wird über einen weiten Oberflächenbereich für Spannungsentlastung gesorgt. Es ist zumindest eine Aussparung an der Oberfläche angeordnet. Durch die zumindest eine Aussparung entsteht vor allem in Verbindung mit den Schlitzen eine optimierte Geometrie, durch die sich eine bessere Wärmeverteilung in dem Werkstoff des Brennstoffverteilerrings ergibt. Durch die bessere Wärmeverteilung treten keine lokal überhöhten Spannungen mehr auf und die verlangten Lebensdauerzyklen können erreicht werden. Die Spannung kann somit in diesem Bereich von ursprünglich von über 950MPa auf 600MPa reduziert werden.According to the invention, at least one slot is now present on the surface between the fuel nozzles. Through this discharge slot results in a better heat distribution in the material of the fuel distributor, whereby the voltages are reduced and sets a longer life expectancy. The relief slot can vary in depth, width and length and be adapted to the respective Brennstoffverteilerring. The at least one slot extends on the surface from the outside to the inside. Thus, stress relief is provided over a wide surface area. At least one recess is arranged on the surface. Due to the at least one recess, especially in connection with the slots, an optimized geometry results, which results in a better heat distribution in the material of the fuel distributor ring. Due to the better heat distribution no locally excessive voltages occur and the required service life cycles can be achieved. The voltage can thus be reduced in this range from originally over 950MPa to 600MPa.

Die zumindest eine Aussparung umfasst teilweise auch die Außenseite des Brennstoffverteilerrings. In bevorzugter Ausgestaltung ist die zumindest eine Aussparung im Wesentlichen rund.The at least one recess also partially includes the outside of the fuel distributor ring. In a preferred embodiment, the at least one recess is substantially round.

In bevorzugter Ausgestaltung sind mehrere Brennstoffdüsen vorhanden, wobei zwischen jeder benachbarten Brennstoffdüse ein Schlitz vorhanden ist. Somit wird der gesamte Oberflächenring des Brennstoffverteilerrings mit Entlastungsschlitzen überzogen.In a preferred embodiment, a plurality of fuel nozzles are present, wherein between each adjacent fuel nozzle, a slot is present. Thus, the entire surface ring of the fuel distributor ring is coated with relief slots.

Bevorzugt-ist der zumindest eine Schlitz im Wesentlichen y-förmig. Dabei umfasst der zumindest eine y-förmige Schlitz zwei Arme und ein Bein, wobei die zwei Arme des im Wesentlichen y-förmigen Schlitzes zu der Außenseite des Brennstoffverteilerrings weisen. Alternativ oder zusätzlich, z.B. in alternierender Reihenfolge, können die zwei Arme des im Wesentlichen y-förmigen Schlitzes auch zu der Innenseite des Brennstoffverteilerrings weisen.Preferably, the at least one slot is substantially Y-shaped. In this case, the at least one Y-shaped slot comprises two arms and one leg, wherein the two arms of the substantially Y-shaped slot point to the outside of the fuel distributor ring. Alternatively or additionally, e.g. in alternate order, the two arms of the substantially y-shaped slot may also point to the inside of the fuel distributor ring.

Die zumindest eine Aussparung kann dabei einen Radius aufweisen, wobei der Radius in Strömungsrichtung gesehen abnimmt.The at least one recess may have a radius, wherein the radius decreases seen in the flow direction.

Bevorzugt umfasst der Brennstoffverteilerring zumindest eine Nickellegierung, insbesondere eine Nickel-MolybdänLegierungen, oder eine Nickel-Chrom-Eisen- MolybdänLegierungen. Diese Legierungen sind besonders hochtemperaturbeständig.The fuel distributor ring preferably comprises at least one nickel alloy, in particular a nickel-molybdenum alloy, or a nickel-chromium-iron-molybdenum alloy. These alloys are particularly resistant to high temperatures.

Bevorzugt umfasst der Brennstoffverteilerring in seinem Inneren zumindest zwei Brennstoffkanäle für zwei Verbrennungsstufen A und B. In vorteilhafter Ausgestaltung umfassen die zwei Brennstoffkanäle zwei Versorgungsanschlüsse. Dadurch können den Brennstoffdüsen jeweils separat und in Abhängigkeit vom Lastzustand der Maschine Brennstoffe zugeführt werden.Preferably, the fuel distributor ring comprises in its interior at least two fuel channels for two combustion stages A and B. In an advantageous embodiment, the two fuel channels comprise two supply connections. As a result, the fuel nozzles can be supplied separately and separately depending on the load state of the engine fuels.

Die Brenneranordnung ist insbesondere in einer Gasturbine vorgesehen. Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren.

Figur 1
zeigt eine Gasturbine in einer stark schematisierten Darstellung,
Figur 2
zeigt einen Gasturbinenbrenner mit Brenneranordnung in einer perspektivischen Darstellung,
Figur 3
zeigt einen Gasturbinenbrenner mit erfindungsgemäßer Brenneranordnung in einer perspektivischen Darstellung,
Figur 4
zeigt eine erfindungsgemäße Brenneranordnung im Schnitt,
Figur 5
zeigt eine erfindungsgemäße Brenneranordnung in der Draufsicht.
The burner arrangement is provided in particular in a gas turbine. Further features, properties and advantages of the present invention will become apparent from the following description of embodiments with reference to the accompanying figures.
FIG. 1
shows a gas turbine in a highly schematic representation,
FIG. 2
shows a gas turbine burner burner assembly in a perspective view,
FIG. 3
shows a gas turbine burner with burner assembly according to the invention in a perspective view,
FIG. 4
shows a burner assembly according to the invention in section,
FIG. 5
shows a burner assembly according to the invention in plan view.

Nachfolgend wird anhand von Figur 1, die eine stark schematisierte Schnittansicht einer Gasturbine zeigt, der Aufbau und die Funktion einer Gasturbine erläutert. Die Gasturbine 1 umfasst einen Verdichterabschnitt 3, einen Verbrennungsabschnitt 4, der im vorliegenden Ausführungsbeispiel eine Mehrzahl von Rohrbrennkammern 5 mit daran angeordneten Brennern 6 umfasst, grundsätzlich aber auch eine Ringbrennkammer umfassen kann, und einen Turbinenabschnitt 7. Ein Rotor 9, auch Läufer genannt, erstreckt sich durch alle Abschnitte und trägt im Verdichterabschnitt 3 Verdichterschaufelkränze 11 und im Turbinenabschnitt 7 Turbinenschaufelkränze 13. Zwischen benachbarten Verdichterschaufelkränzen 11 und zwischen benachbarten Turbinenschaufelkränzen 13 sind Kränze aus Verdichterleitschaufeln 15 bzw. Kränze aus Turbinenleitschaufeln 17 angeordnet, die sich von einem Gehäuse 19 der Gasturbine 1 aus radial in Richtung auf den Rotor 9 erstrecken.The following is based on 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. Between adjacent compressor blade rings 11 and between adjacent turbine blade rings 13 are wreaths of compressor vanes 15 and wreaths of turbine vanes 17 arranged, extending from a housing 19 of the gas turbine 1 from extend radially in the direction of the rotor 9.

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 air inlet 21 into the compressor section 3. There, the air is compressed by the rotating compressor blades 11 and directed to the burners 6 in the combustion section 4. In the burners 6, the air is gaseous or mixed liquid fuel and the mixture burned in the combustion chambers 5. The hot combustion exhaust gases under high pressure are then supplied as working medium to the turbine section 7. On their way through the turbine section, the combustion exhaust gases impart impulses to the turbine blades 13, relaxing and cooling. Finally, the expanded and cooled combustion exhaust gases exit the turbine section 7 through an exhaust 23. The transmitted pulse results in a rotational movement of the rotor that drives the compressor and a consumer, such as an electric current generator or an industrial machine. The rings of turbine vanes 17 serve as nozzles for conducting the working medium in order to optimize the momentum transfer to the turbine blades 13.

Figur 2 zeigt einen Brenner 6 des Verbrennungsabschnitts 4 in einer perspektivischen Darstellung. Als Hauptkomponenten umfasst der Brenner 6 einen Brennstoffverteilerring 27, acht Brennstoffdüsen 29, die sich vom Brennstoffverteilerring 27 aus erstrecken und acht im Bereich der Spitzen der Brennstoffdüsen 29 angeordnete Drallerzeuger 31. Der Brennstoffverteilerring 27 und die Brennstoffdüsen 29 bilden zusammen ein Brennergehäuse, durch welches sich Brennstoffleitungen zu Eindüsöffnungen erstrecken, die innerhalb der Drallerzeuger 31 angeordnet. Die Brennstoffdüsen 29 können am Brennstoffverteilerring 27 angeschweißt sein. Über eine Anzahl von Rohrstutzen (nicht dargestellt) kann der Brenner an Brennstoffzufuhrleitungen angeschlossen werden. Mittels eines Flansches 35 lässt sich der Brenner 6 an einer Rohrbrennkammer so befestigen, dass die Brennstoffdüsen 29 zum Brennkammerinneren hin zeigen. FIG. 2 shows a burner 6 of the combustion section 4 in a perspective view. As main components, the burner 6 comprises a fuel distributor ring 27, eight fuel nozzles 29 extending from the fuel distributor ring 27 and eight swirlers 31 arranged in the region of the tips of the fuel nozzles 29. The fuel distributor ring 27 and the fuel nozzles 29 together form a burner housing through which fuel lines extend to Eindüsöffnungen disposed within the swirl generator 31. The fuel nozzles 29 may be welded to the fuel distributor ring 27. Through a number of pipe sockets (not shown), the burner can be connected to fuel supply lines. By means of 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.

Obwohl der in Figur 2 gezeigte Brenner 6 acht Brennstoffdüsen 29 aufweist, ist es auch möglich, ihn mit einer anderen Zahl an Brennstoffdüsen 29 auszustatten. Die Zahl an Brennstoffdüsen 29 kann dabei größer oder kleiner als acht sein, beispielsweise können sechs Brennstoffdüsen 29 oder zwölf Brennstoffdüsen 29 vorhanden sein, die jeweils einen eigenen Drallerzeuger aufweisen. Weiterhin ist üblicherweise eine Pilotbrennstoffdüse im Zentrum des Brenners angeordnet. Die Pilotbrennstoffdüse ist der Übersichtlichkeit halber in Figur 2 nicht dargestellt.Although the in FIG. 2 As shown 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 29 may be greater than or less than eight, for example, six fuel nozzles 29 or twelve fuel nozzles 29 be present, each having its own swirl generator. Furthermore, 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.

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 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.

Der Brennstoffverteilerring 27 hat die Aufgabe den Brennstoff auf die Brennstoffdüsen 29 zu verteilen. Er ist dazu im inneren mit zwei Brennstoffkanälen 41,42 versehen, wovon jeder eine Anzahl von Düsen 29 (in diesem speziellen Fall jeweils 4 Düsen 29) mit Brennstoff als eine Stufe A und eine Stufe B versorgt (Figur 3 und Figur 4). Die zwei Brennstoffkanäle 41 und 42 umfassen zwei Versorgungsanschlüsse 51,52 zur Zuführung von Brennstoff. Dabei kann es sich auch um unterschiedliche Brennstoffarten handeln. Der Brennstoffverteilerring 27 wird von außen mit bis zu 500°C warmer Verdichterluft umströmt, jedoch von innen mit kaltem Brennstoff, der im Extremfall lediglich eine Temperatur von 20 °C aufweisen kann. Dadurch treten an dem Brennstoffverteilerring 27 sehr hohe Spannungen auf. Vor allem auf der den Düsen 29 zugewandten Oberflächenseite 54 des Brennstoffverteilerrings 27 treten sehr hohe Spannungen auf, so dass die Lebensdauer nicht erreicht werden kann.The fuel distributor ring 27 has the task of distributing the fuel to the fuel nozzles 29. It is internally provided with two fuel channels 41, 42 each of which supplies a number of nozzles 29 (4 nozzles 29 in this particular case) with fuel as a stage A and a stage B ( FIG. 3 and FIG. 4 ). The two fuel passages 41 and 42 include two supply ports 51, 52 for supplying fuel. These can also be different types of fuel. The fuel distributor ring 27 flows from the outside with up to 500 ° C warm compressor air, but from the inside with cold fuel, which in extreme cases can only have a temperature of 20 ° C. As a result, very high voltages occur at the fuel distributor ring 27. Especially on the nozzles 29 facing surface side 54 of the fuel distributor ring 27 occur very high voltages, so that the life can not be achieved.

Es ist eine Anzahl von Brennstoffdüsen 29 vorhanden, welche in Strömungsrichtung an den Brennstoffverteilerring 27 montiert sind. Zudem weist der Brennstoffverteilerring 27 in Strömungsrichtung eine ringförmige Oberfläche 54 und eine zur Ringmitte weisende äußere Innenseite 56 und eine gegenüberliegende äußere Außenseite 58 auf.There are a number of fuel nozzles 29 which are mounted in the flow direction to the fuel distributor ring 27. In addition, the fuel distributor ring 27 has an annular surface 54 in the flow direction and an outer inner side 56 pointing to the middle of the ring and an outer outer side 58 opposite to it.

Erfindungsgemäß ist nun auf der Oberfläche 54 zwischen den Brennstoffdüsen 29 zumindest ein Schlitz 60 vorhanden. Dieser ist wesentlich y-förmig (Figur 3 und Figur 5). Dabei bedeutet im Wesentlichen y-förmig, dass hier alle Formen umfasst sind, die annähernd an den Buchstaben Y erinnern, das heißt zwei Arme 62 und ein Bein 63 aufweisen. Vorteilhafterweise sind alle Zwischenräume auf der Oberfläche 54 zwischen den Düsen 29 mit solchen Schlitzen 60 versehen. Der Schlitz 60, und insbesondere der y-förmige Schlitz 60 erstreckt sich auf der Oberfläche 54 von der Außenseite 58 bis zur Innenseite 56. Somit lässt sich der hohe thermische Gradient bei Betrieb und dadurch entstehende Spannungen vermeiden. Damit wird die Lebensdauer der Brenneranordnung, insbesondere des Brennstoffverteilerrings 27 wesentlich erhöhen.According to the invention, at least one slot 60 is now present on the surface 54 between the fuel nozzles 29. This is essentially y-shaped ( FIG. 3 and FIG. 5 ). In this case, substantially Y-shaped means that all forms are here encompassed which approximately remind one of the letter Y, that is to say have two arms 62 and one leg 63. Advantageously, all spaces on the surface 54 between the nozzles 29 are provided with such slots 60. The slot 60, and in particular the y-shaped slot 60 extends on the surface 54 from the outside 58 to the inside 56. Thus, the high thermal gradient can be avoided during operation and resulting stresses. Thus, the life of the burner assembly, in particular the fuel distributor ring 27 will increase significantly.

Dabei können die zwei Arme 62 des im Wesentlichen y-förmigen Schlitzes 60 vorteilhafterweise an der Außenseite 58 der Oberfläche 54 des Brennstoffverteilerrings 27 angeordnet sind. Es können aber auch die zwei Arme 62 des im Wesentlichen y-förmigen Schlitzes 60 zu der Innenseite 56 der Oberfläche 54 des Brennstoffverteilerrings 27 weisen. Auch alternierende Reihenfolgen sind möglich.In this case, the two arms 62 of the substantially Y-shaped slot 60 can advantageously be arranged on the outside 58 of the surface 54 of the fuel distributor ring 27. However, it is also possible for the two arms 62 of the substantially Y-shaped slot 60 to point to the inside 56 of the surface 54 of the fuel distributor ring 27. Alternate sequences are possible.

Zusätzlich sind Aussparungen 66 an der Oberfläche 54 angeordnet (Figur 5). Diese Aussparungen 66 sind an der Oberfläche 54 so angeordnet, dass sie teilweise auch die Außenseite 58 des Brennstoffverteilerrings 27 umfassen, dass heißt, es ist eine Aussparung von der Außenseite 58 des Brennstoffverteilers 27 vorhanden. Die Aussparung 66 kann in ihrer Tiefe und in Form variieren. Bevorzugt handelt es sich dabei jedoch um eine im Wesentlichen runde Aussparung 66.In addition, recesses 66 are arranged on the surface 54 (FIG. FIG. 5 ). These recesses 66 are arranged on the surface 54 such that they partially also include the outside 58 of the fuel distributor ring 27, that is, there is a recess from the outside 58 of the fuel distributor 27. The recess 66 may vary in depth and shape. However, this is preferably a substantially circular recess 66.

Dabei kann die Aussparungen 66 einen Radius aufweisen und der Radius in Strömungsrichtung gesehen abnehmen. Somit lässt sich noch effektiver der hohe thermische Gradient bei Betrieb und dadurch entstehende Spannungen vermeiden.In this case, the recesses 66 may have a radius and the radius seen in the flow direction decrease. This makes it even more effective to avoid the high thermal gradient during operation and the resulting stresses.

Bevorzugt umfasst der Brennstoffverteilerring 27 zumindest eine Nickellegierung, insbesondere eine Nickel-MolybdänLegierungen. Dieser Werkstoff ist besonders hitzebeständig und damit für Brenner besonders gut geeignet.The fuel distributor ring 27 preferably comprises at least one nickel alloy, in particular a nickel-molybdenum alloy. This material is particularly heat-resistant and therefore particularly suitable for burners.

Die erfindungsgemäße Brenneranordnung kann insbesondere in einer Gasturbine eingesetzt werden.The burner assembly according to the invention can be used in particular in a gas turbine.

Durch den zumindest einen erfindungsgemäßen Schlitz 60 auf der Oberfläche 54 des Brennstoffverteilerrings 27 zwischen den Brennstoffdüsen 29 und der Aussparung lassen sich betriebsbedingte hohe Spannungen am Brennstoffverteilerring 27 vermeiden.Due to the at least one slot 60 according to the invention on the surface 54 of the fuel distributor ring 27 between the fuel nozzles 29 and the recess, high operating voltages on the fuel distributor ring 27 can be avoided.

Durch diese wesentlich bessere Geometrie des Brennstoffverteilerrings 27 ergibt sich eine verbesserte Wärmeverteilung in dem Brennstoffverteilerring-Werkstoff. Durch die bessere Wärmeverteilung treten lokal keine überhöhten Spannungen mehr auf. Wesentlich verlängerte Lebenszyklen sind die Folge.This significantly better geometry of the fuel distributor ring 27 results in improved heat distribution in the fuel distributor ring material. Due to the better heat distribution no excessively high voltages occur locally. Significantly extended life cycles are the result.

Es ist daher möglich, die Spannungen in diesem Bereich von über 950 MPa auf 600 MPa zu verbessern.It is therefore possible to improve the stresses in this range from over 950 MPa to 600 MPa.

Diese erfindungsgemäßen Schlitze 60 und Aussparungen 66 können fertigungstechnisch in bereits bestehende Brennstoffverteilerringe 27 eingebaut werden, da sie keine tiefgreifenden Umbauten erfordert und ist somit fertigungstechnisch leicht umzusetzen. Auch auf die bisherige Aero-Performance des Brenners entsteht lediglich minimaler Einfluss.These slots 60 and recesses 66 according to the invention can be built into existing fuel distributor rings 27 in terms of production technology, since they do not require any far-reaching conversions and are therefore easy to implement in terms of manufacturing technology. Even on the previous aero performance of the burner creates only minimal impact.

Claims (12)

  1. Burner assembly having
    - a fuel distribution ring (27),
    - a number of fuel nozzles (29) which are mounted on the fuel distribution ring (27) in the flow direction,
    - wherein the fuel distribution ring (27) comprises an annular surface (54) in the flow direction,
    - wherein the fuel distribution ring comprises an outer inner side (56) oriented toward the ring centre and an opposite outer outer side (58),
    characterised in that
    - at least one slot (60) exists on the surface (54) between the fuel nozzles (29), and wherein the at least one slot (60) on the surface (54) extends from the outer side (58) to the inner side (56),
    and wherein at least one recess (66) is arranged on the surface (54) and the at least one recess (66) partially also includes the exterior (58) of the fuel distributor (27).
  2. Burner assembly according to claim 1, characterised in that
    several fuel nozzles (29) exist, wherein a slot (60) is present between each adjacent fuel nozzle (29).
  3. Burner assembly according to claim 1 - 2, characterised in that
    the at least one slot (60) is essentially y-shaped.
  4. Burner assembly according to claim 3, characterised in that
    the at least one y-shaped slot includes two arms (62) and a leg (63) and the two arms (62) of the essentially y-shaped slot (60) orientate towards the outer side (58) of the burner distribution ring (27).
  5. Burner assembly according to claim 4, characterised in that
    the at least one y-shaped slot (60) includes two arms (62) and a leg (63) and the two arms (62) of the essentially y-shaped slot (60) orient toward the inner side (56) of the fuel distribution ring (27).
  6. Burner assembly according to one of the preceding claims, characterised in that
    the at least one recess (66) is essentially round.
  7. Burner assembly according to one of the preceding claims, characterised in that the at least one recess (66) includes a radius and the radius reduces when viewed in the flow direction.
  8. Burner assembly according to one of the preceding claims, characterised in that
    the fuel distribution ring (27) includes at least one nickel alloy.
  9. Burner assembly according to claim 8, characterised in that
    the fuel distribution ring (27) includes at least one nickel molybdenum alloy.
  10. Burner assembly according to one of the preceding claims, characterised in that
    the fuel distribution ring (27) includes at least two fuel channels (41, 42) for two combustion stages A and B in its interior.
  11. Burner assembly according to one of the preceding claims, characterised in that the two fuel channels (41, 42) include two supply connections (51, 52).
  12. Gas turbine having a burner assembly according to one of the preceding claims.
EP10779300.2A 2009-11-30 2010-11-08 Burner assembly Not-in-force EP2507557B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10779300.2A EP2507557B1 (en) 2009-11-30 2010-11-08 Burner assembly

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09177514A EP2327933A1 (en) 2009-11-30 2009-11-30 Burner assembly
EP10779300.2A EP2507557B1 (en) 2009-11-30 2010-11-08 Burner assembly
PCT/EP2010/067000 WO2011064086A1 (en) 2009-11-30 2010-11-08 Burner assembly

Publications (2)

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EP2507557A1 EP2507557A1 (en) 2012-10-10
EP2507557B1 true EP2507557B1 (en) 2013-09-25

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EP09177514A Withdrawn EP2327933A1 (en) 2009-11-30 2009-11-30 Burner assembly
EP10779300.2A Not-in-force EP2507557B1 (en) 2009-11-30 2010-11-08 Burner assembly

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US (1) US9103552B2 (en)
EP (2) EP2327933A1 (en)
CN (1) CN102639939B (en)
ES (1) ES2432237T3 (en)
RU (1) RU2562900C2 (en)
WO (1) WO2011064086A1 (en)

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US20120234010A1 (en) 2012-09-20
CN102639939A (en) 2012-08-15
EP2507557A1 (en) 2012-10-10
EP2327933A1 (en) 2011-06-01
US9103552B2 (en) 2015-08-11
WO2011064086A1 (en) 2011-06-03
CN102639939B (en) 2014-11-12
RU2562900C2 (en) 2015-09-10
ES2432237T3 (en) 2013-12-02
RU2012127366A (en) 2014-01-10

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