EP2470834A1 - Burner, in particular for gas turbines - Google Patents

Burner, in particular for gas turbines

Info

Publication number
EP2470834A1
EP2470834A1 EP10749631A EP10749631A EP2470834A1 EP 2470834 A1 EP2470834 A1 EP 2470834A1 EP 10749631 A EP10749631 A EP 10749631A EP 10749631 A EP10749631 A EP 10749631A EP 2470834 A1 EP2470834 A1 EP 2470834A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
swirl
nozzles
burner according
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.)
Granted
Application number
EP10749631A
Other languages
German (de)
French (fr)
Other versions
EP2470834B1 (en
Inventor
Andreas Böttcher
Mariano Cano Wolff
Andre Kluge
Tobias Krieger
Sascha Staring
Ulrich Wörz
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
Publication of EP2470834A1 publication Critical patent/EP2470834A1/en
Application granted granted Critical
Publication of EP2470834B1 publication Critical patent/EP2470834B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/36—Supply of different fuels

Definitions

  • the present invention relates to a burner and, more particularly, to a gas turbine combustor having a central fuel supply arrangement.
  • the invention relates to a gas turbine.
  • the burner described in EP 0 276 696 B1 is a hybrid burner for premixing operation with gas and / or oil, as it is used in particular for gas turbine plants.
  • the burner comprises a central fuel supply arrangement, in which also a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • the possibility for feeding in inert materials is provided.
  • the central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with a swirler blading therein having a plurality of blades and gas pre-mixing nozzle pipes located upstream of the blades.
  • inlet nozzles for oil in the area of the swirl blading which allow premixing of the main air flow with oil.
  • the fuel gas can also be injected into the air duct through nozzle openings arranged in the swirl vanes themselves, as described, for example, in EP 0 580 683 B1.
  • Fuel injection through the blade as in EP 0 580 683 Bl further fuel injection can be used by the blade.
  • This additional fuel injection should be controllable separately from the main gas stage, i.
  • an additional, second gas channel must be introduced into the central fuel supply device of the burner.
  • a difficulty now is that the additional gas channel meets the necessary strength criteria, while having a long life.
  • the object of the present invention is therefore to provide a burner, in particular a gas turbine burner, with two fuel passages which has a long service life. It is a second object of the present invention to provide an advantageous gas turbine.
  • the first object is achieved by the specification of a burner according to claim 1, the second object by a gas turbine according to claim 8.
  • the dependent claims contain advantageous embodiments of the invention.
  • a burner has a central fuel supply arrangement and an annular air duct surrounding the central fuel supply arrangement for supplying combustion air.
  • swirl vanes are arranged, which first fuel nozzles for injecting a substantially gaseous fuel into the combustion air and second fuel nozzles for injecting a substantially gaseous Have fuel in the combustion air.
  • the first fuel nozzles are fed by a fuel distributor supply in the fuel supply arrangement and the second fuel nozzles by a fuel distributor channel in the fuel supply arrangement.
  • the burner has a fuel flow direction.
  • the fuel distributor supply now comprises a supply pipe, which is connected downstream with the swirl blade, and a ring attachment, wherein the supply pipe is connected upstream with the ring attachment and wherein the ring attachment is arranged upstream of the fuel distribution channel.
  • This causes a spatial separation of the two fuel passages, that is, the feed tube with the ring attachment and the original fuel distribution channel are spatially separated.
  • the original fuel distribution channel is more or less parallel to the supply pipe.
  • the ring attachment acts to pull out the high voltages from the component, that is, the fuel supply assembly and distribute it evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the fuel supply assembly is significantly extended.
  • the original aero design is not or only insignificantly influenced.
  • already manufactured machines can be easily provided with such a ring attachment and such a feed tube due to the now easier production and now easier installation.
  • the ring attachment comprises a separate pipe connection. This supplies the feed pipe with fuel.
  • a plurality of swirl vanes are provided, each of these swirl vanes having a separate supply pipe, wherein each of the separate supply pipes is connected to the one ring attachment.
  • the first fuel injection is fed by a first manifold and the second fuel injection is fed by a second manifold, the manifold being integrated in the swirl vane, and wherein the swirl vane between the first and second manifolds is split into two vane halves.
  • the distribution pipes and the respective nozzles can be supplied separately with fuel. As a result, a controlled control of the fuel flow is possible.
  • Both blade halves preferably have a locating pin downstream and a sliding seat upstream. By the dowel pin and the sliding seat, the two blade halves are now thermally separately expandable, which also stresses are reduced.
  • the fuel distribution channel and the supply pipe are separated by a web, wherein the web is made flexible.
  • the web can be made of an elastic material and / or it can also act elastically by means of a corresponding geometric design and thus compensate for stresses. This can be effected for example by a curved or corrugated web.
  • a burner is provided in a gas turbine.
  • FIG. 2 shows a schematic diagram of a swirl blade
  • FIG. 3 shows a schematic diagram of a combustion chamber hub with two integrated gas stages and an oil channel
  • FIG 4 shows a cross section of a combustion chamber hub according to the invention with ring attachment and swirl blade
  • FIG 5 is a plan view of a ring attachment with swirl blades.
  • FIG. 1 shows a burner in a highly schematized schematic diagram.
  • the burner which may optionally be used in conjunction with a plurality of similar burners, for example in the combustion chamber of a gas turbine plant, comprises an inner pilot burner system and a main burner system concentrically surrounding the pilot burner system. Both the pilot burner system and the main burner system may optionally be operated with gaseous and / or liquid fuels, such as natural gas or fuel oil.
  • the pilot burner system includes an inner oil supply passage 1 which may be concentrically surrounded by an inner annular gas supply passage 3. This, in turn, can be be surrounded concentrically surrounding air supply channel or Inertstoffzubuchkanal 5.
  • a suitable ignition system may be arranged in or on this air supply channel (not shown in the figure).
  • the pilot burner system has a combustion chamber 7 zuwerende outlet opening 9, in whose area a twist blading 11 may be arranged in the air supply duct. Gas can be injected from the inner gas supply channel 3 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 5 by means of nozzle openings 13. Oil from the oil supply channel can be injected into the supplied air or the added inert material by means of oil nozzles 15 downstream of the swirl blading.
  • the pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame.
  • a diffusion burner in which the fuel is injected directly into the flame.
  • the main burner system surrounding the pilot burner system comprises a radial outer air supply channel 17, also called an annular air channel, through which swirl blades 19 of a swirl blading extend.
  • These swirl blades 19 have first fuel nozzles 21 and second fuel nozzles 23, through which fuel gas can be injected into the air flowing in through the radial air supply channel 17.
  • oil can be injected by means of oil nozzles 25.
  • the first fuel nozzles 21 and second fuel nozzles 23 located in the swirl blades 19 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 27.
  • the Swirl vane 19 and the hub 27 have a fuel flow direction.
  • this first and second annular fuel distributor channels 29 and 31 are arranged, which supply the fuel nozzles 21 and 23 with gas.
  • an annular oil distribution channel 33 is arranged, which supplies the oil nozzles 25 with oil.
  • the fuel distributor channels 29, 31 and the oil distribution channel 33 are supplied with fuel via fuel supply channels 35, 37 or via an oil supply channel 39.
  • the fuel supply channels 35, 37 supply the fuel distribution channels 29, 31 with fuel.
  • For the oil supply channel 39 is a separate oil supply pipe 43 before.
  • FIG. 2 shows a schematic representation of a swirl blade 19 with two integrated gas stages B and D.
  • the swirl blade 19 has two independent
  • the one fuel distribution channel 29 with the outlet nozzles 21 can be used, for example, for injecting a different medium D than the second fuel distribution channel 31 via the outlet nozzles 23 (medium B).
  • both media to be injected through the fuel distribution channels 29 and 31 of the swirl vane 19 will be gaseous, e.g. As the one medium natural gas and the other medium coal gas.
  • an inert material such as water vapor can be injected via these outlet nozzles 21 and / or 23 if necessary.
  • FIG. 3 shows a fuel hub 27 with the fuel distributor channel 29 and 31 with openings, which leads the fuel into the blade 19.
  • the two fuel distribution channels 29 and 31 are arranged substantially parallel and separated by a web 50.
  • At least one of the fuel distributor channels 29 is then designed as a feed tube 55 (FIG. 4).
  • the feed tube 55 opens downstream into a manifold 65 (or alternatively 70). Upstream, the feed tube 55 is connected to the ring attachment 60 ( Figure 5).
  • the ring attachment 60 seen in the flow direction, the fuel distribution channel 31 (or alternatively 29) upstream.
  • the original fuel distribution channel 31 is parallel to the supply pipe 55.
  • the ring attachment 60 is supplied with a separate pipe connection 75.
  • the original fuel distribution channel 31 (or alternatively 29) is supplied with another channel 80.
  • the two leading gas passages namely the feed tube 55 with the ring attachment 60 and the original fuel distribution channel 31 (or alternatively 29) according to the invention spatially decoupled.
  • the ring attachment 60 acts to pull the high stresses out of the hub 27 and distribute them evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the burner hub 27 is substantially extended.
  • the ring attachment 60 does not or only insignificantly influences the original aero design. Also already manufactured machines can easily be provided with such a ring attachment 60 and such a feed tube 55 due to the now easier production and now easier installation.
  • Such a burner hub 27 is preferably used in conjunction with a divided swirl blade 19.
  • This comprises the first fuel injection 21, which is fed by a first distributor pipe 65, and the second fuel injection 23, which is fed by a second distributor pipe 70.
  • the manifold 65, 70 integrated in the swirl blade 19.
  • the split swirl vane 19 is now interposed between the first and second manifolds 65 and 70 divided into two vane halves 19a, 19b.
  • the blade halves 19a, 19b also have downstream of a fitting pin 90a, 90b and upstream of a sliding seat 85a, 85b, which is mounted so to speak in the hub 27 itself.
  • the web 50 in order to obtain an additional voltage reduction, can be made flexible.
  • the web 50 can be made of an elastic material. Additionally or alternatively, the web 50 can also act elastically by a corresponding geometry and thus compensate for stresses. This can e.g. be effected by a curved or corrugated web 50.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

The invention relates to a burner comprising a central fuel supply arrangement (27), an annular air channel (18) surrounding said central fuel supply arrangement (27), for supplying combustion air and swirl blades which are arranged in the annular air channel (17), comprising first fuel nozzles (21) for introducing an essentially gaseous fuel into the combustion air, and second fuel nozzles (23) for introducing an essentially gaseous fuel into the combustion air. The first fuel nozzles (21) are supplied by a fuel distributor supply in the fuel supply arrangement (27), and the second fuel nozzles (23) are supplied by a fuel distributor channel (31) in the fuel supply arrangement (27). The fuel distributor supply comprises a supply pipe (55) which is connected downstream of the swirl blade (19), and an annular attachment (60). The supply pipe (55) is connected downstream of the annular attachment (60) and said annular attachment (60) is mounted upstream of the fuel distributor channel (31) when seen in the direction of flow. The invention also relates to a gas turbine comprising said type of burner.

Description

Beschreibung description
Brenner, insbesondere für Gasturbinen Die vorliegende Erfindung betrifft einen Brenner und insbesondere einen Gasturbinenbrenner mit einer zentralen Brennstoffzufuhranordnung. Daneben betrifft die Erfindung eine Gasturbine . Im Hinblick auf die weltweiten Bemühungen zur Senkung desBurner, particularly for gas turbines The present invention relates to a burner and, more particularly, to a gas turbine combustor having a central fuel supply arrangement. In addition, the invention relates to a gas turbine. With regard to the global efforts to reduce the
Schadstoffausstoßes von Befeuerungsanlagen, insbesondere bei Gasturbinen, wurden in den letzten Jahren Brenner entwickelt, die besonders geringe Ausstöße an Stickoxiden (NOx) aufweisen. Dabei wird vielfach Wert darauf gelegt, dass solche Brenner jeweils nicht nur mit einem Brennstoff, sondern möglichst mit verschiedenen Brennstoffen, beispielsweise Öl und Erdgas wahlweise oder in Kombination betreibbar sind, um die Versorgungssicherheit und Flexibilität des Betriebs zu erhöhen. Solche Brenner sind beispielsweise in der EP 0 276 696 Bl beschrieben. Pollutant emissions from lighting systems, especially in gas turbines, have been developed in recent years burners that have particularly low emissions of nitrogen oxides (NOx). It is often emphasized that such burners are not only with a fuel, but possibly with different fuels, such as oil and natural gas, either selectively or in combination operable to increase the security of supply and flexibility of operation. Such burners are described, for example, in EP 0 276 696 B1.
Der in EP 0 276 696 Bl beschriebene Brenner ist ein Hybridbrenner für Vormischbetrieb mit Gas und/oder Öl, wie er insbesondere für Gasturbinenanlagen angewendet wird. Der Brenner umfasst eine zentrale Brennstoffzufuhranordnung, in die auch ein Pilotbrennersystem integriert ist, welches mit Gas und/oder Öl als ein sogenannter Diffusionsbrenner oder als gesonderter Vormischbrenner betreibbar ist. Zusätzlich ist die Möglichkeit zur Einspeisung von Inertstoffen vorgesehen. Die zentrale Brennstoffzufuhranordnung ist von einem Hauptbrennersystem umgeben, welches ein Luftzufuhr-Ringkanalsystem mit einer darin befindlichen Drallbeschaufelung mit einer Mehrzahl von Schaufeln und stromauf von den Schaufeln angeordneten Düsenrohren für den Vormischbetrieb mit Gas auf- weist. Zusätzlich sind in der Brennstoffzufuhranordnung Einlassdüsen für Öl im Bereich der Drallbeschaufelung vorhanden, die eine Vormischung des Hauptluftstroms mit Öl ermöglichen. Statt wie in EP 0 276 696 Bl mittels stromauf von den Drallschaufeln gelegener Düsenrohre kann das Brenngas auch durch in den Drallschaufeln selbst angeordnete Düsenöffnungen in den Luftkanal eingedüst werden, wie dies beispielsweise in EP 0 580 683 Bl beschrieben ist. The burner described in EP 0 276 696 B1 is a hybrid burner for premixing operation with gas and / or oil, as it is used in particular for gas turbine plants. The burner comprises a central fuel supply arrangement, in which also a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner. In addition, the possibility for feeding in inert materials is provided. The central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with a swirler blading therein having a plurality of blades and gas pre-mixing nozzle pipes located upstream of the blades. In addition, in the fuel supply arrangement there are inlet nozzles for oil in the area of the swirl blading, which allow premixing of the main air flow with oil. Instead of EP 0 276 696 B1 by means of nozzle tubes located upstream of the swirl vanes, the fuel gas can also be injected into the air duct through nozzle openings arranged in the swirl vanes themselves, as described, for example, in EP 0 580 683 B1.
Um die Kontrolle der Emissionen und der Verbrennungsstabilität zukünftig noch zu erhöhen, soll zusätzlich zu einer In order to increase the control of emissions and combustion stability in the future, in addition to a
Brennstoffeindüsung durch die Schaufel wie in EP 0 580 683 Bl eine weitere Brennstoffeindüsung durch die Schaufel genutzt werden. Diese zusätzliche Brennstoffeindüsung soll separat von der Hauptgasstufe regelbar sein, d.h. es muss zusätzlich zu den bisher bestehenden Gas- und Ölkanälen ein zusätzlicher, zweiter Gaskanal in die zentrale Brennstoffzuführein- richtung des Brenners eingebracht werden. Eine Schwierigkeit besteht nun darin, dass der zusätzliche Gaskanal die notwendigen Festigkeitskriterien erfüllt, und gleichzeitig eine lange Lebensdauer aufweist. Aufgabe der vorliegenden Erfindung ist es daher, einen Brenner, insbesondere einen Gasturbinenbrenner, zur Verfügung zu stellen mit zwei Brennstoffpassagen, welcher eine lange Lebensdauer aufweist. Es ist eine zweite Aufgabe der vorliegenden Erfindung, eine vorteilhafte Gasturbine zur Verfügung zu stellen. Fuel injection through the blade as in EP 0 580 683 Bl further fuel injection can be used by the blade. This additional fuel injection should be controllable separately from the main gas stage, i. In addition to the previously existing gas and oil channels, an additional, second gas channel must be introduced into the central fuel supply device of the burner. A difficulty now is that the additional gas channel meets the necessary strength criteria, while having a long life. The object of the present invention is therefore to provide a burner, in particular a gas turbine burner, with two fuel passages which has a long service life. It is a second object of the present invention to provide an advantageous gas turbine.
Die erste Aufgabe wird durch die Angabe eines Brenners nach Anspruch 1 gelöst, die zweite Aufgabe durch eine Gasturbine nach Anspruch 8. Die abhängigen Ansprüche enthalten vorteil- hafte Ausgestaltungen der Erfindung. The first object is achieved by the specification of a burner according to claim 1, the second object by a gas turbine according to claim 8. The dependent claims contain advantageous embodiments of the invention.
Dabei weist ein Brenner eine zentrale Brennstoffzufuhranord- nung und einen die zentrale Brennstoffzufuhranordnung umgebenden Ringluftkanal zur Zufuhr von Verbrennungsluft auf. In dem Ringluftkanal sind Drallschaufeln angeordnet, welche erste Brennstoffdüsen zum Eindüsen eines im Wesentlichen gasförmigen Brennstoffs in die Verbrennungsluft und zweite Brennstoffdüsen zum Eindüsen eines im Wesentlichen gasförmigen Brennstoffs in die Verbrennungsluft aufweisen. Dabei werden die ersten Brennstoffdüsen von einer Brennstoffverteilerzufuhr in der Brennstoffzufuhranordnung gespeist und die zweiten Brennstoffdüsen von einem Brennstoffverteilerkanal in der Brennstoffzufuhranordnung. Im Betrieb weist der Brenner eine Brennstoff Strömungsrichtung auf. In this case, a burner has a central fuel supply arrangement and an annular air duct surrounding the central fuel supply arrangement for supplying combustion air. In the annular air duct swirl vanes are arranged, which first fuel nozzles for injecting a substantially gaseous fuel into the combustion air and second fuel nozzles for injecting a substantially gaseous Have fuel in the combustion air. In this case, the first fuel nozzles are fed by a fuel distributor supply in the fuel supply arrangement and the second fuel nozzles by a fuel distributor channel in the fuel supply arrangement. In operation, the burner has a fuel flow direction.
Erfindungsgemäß wurde nun erkannt, dass für diese doppelte Schaufeleindüsung deshalb eine Realisierung schwierig ist, da keine ausreichende Lebensdauer für den Gasverteiler, das heißt die Brennstoffzufuhranordnung, vorhanden ist und somit kein sicherer Einsatz gewährleistet werden kann. Weiterhin wurde erkannt, dass hohe Temperaturgradienten zwischen den einzelnen Brennstoffpassagen zu hohen Thermospannungen füh- ren, welche die Lebensdauer stark einschränken. According to the invention it has now been recognized that for this double Schaufeleindüsung therefore a realization is difficult, since no sufficient life for the gas distributor, that is, the fuel supply arrangement, is present and thus no safe use can be guaranteed. Furthermore, it was recognized that high temperature gradients between the individual fuel passages lead to high thermoelectric voltages, which severely limit the service life.
Erfindungsgemäß umfasst nun die Brennstoffverteilerzufuhr ein Zufuhrrohr, welches stromabwärts mit der Drallschaufel verbunden ist, sowie einen Ringaufsatz, wobei das Zufuhrrohr stromaufwärts mit dem Ringaufsatz verbunden ist und wobei der Ringaufsatz in Strömungsrichtung gesehen dem Brennstoffverteilerkanal vorgeschaltet ist. Dies bewirkt eine räumliche Trennung der beiden Brennstoffpassagen, das heißt, das Zufuhrrohr mit dem Ringaufsatz und der ursprüngliche Brenn- stoffverteilerkanal sind räumlich getrennt. Somit ist der ursprüngliche Brennstoffverteilerkanal quasi parallel zu dem Zufuhrrohr. Der Ringaufsatz wirkt dahingehend, dass er die hohen Spannungen aus dem Bauteil, das heißt, der Brennstoffzufuhranordnung herauszieht und gleichmäßig über dem Bauteil verteilt. Dadurch ergibt sich eine Entschärfung des Bauraums durch niedrigere Spannungen. Somit wird die Lebensdauer der Brennstoffzufuhranordnung wesentlich verlängert. Durch den Ringaufsatz wird das ursprüngliche Aero-Design nicht oder nur unwesentlich beeinflusst. Auch können bereits gefertigte Ma- schinen leicht mit einem solchen Ringaufsatz und einem solchen Zufuhrrohr aufgrund der nun leichteren Fertigung und des nun leichteren Einbaus versehen werden. Bevorzugt umfasst der Ringaufsatz einen separaten Rohran- schluss. Dieser versorgt das Zufuhrrohr mit Brennstoff. According to the invention, the fuel distributor supply now comprises a supply pipe, which is connected downstream with the swirl blade, and a ring attachment, wherein the supply pipe is connected upstream with the ring attachment and wherein the ring attachment is arranged upstream of the fuel distribution channel. This causes a spatial separation of the two fuel passages, that is, the feed tube with the ring attachment and the original fuel distribution channel are spatially separated. Thus, the original fuel distribution channel is more or less parallel to the supply pipe. The ring attachment acts to pull out the high voltages from the component, that is, the fuel supply assembly and distribute it evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the fuel supply assembly is significantly extended. Due to the ring attachment, the original aero design is not or only insignificantly influenced. Also already manufactured machines can be easily provided with such a ring attachment and such a feed tube due to the now easier production and now easier installation. Preferably, the ring attachment comprises a separate pipe connection. This supplies the feed pipe with fuel.
In bevorzugter Ausgestaltung sind mehrere Drallschaufeln vor- gesehen, wobei jede einzelne dieser Drallschaufeln ein separates Zufuhrrohr aufweist, wobei jedes der separaten Zufuhrrohre mit dem einen Ringaufsatz verbunden ist. In a preferred embodiment, a plurality of swirl vanes are provided, each of these swirl vanes having a separate supply pipe, wherein each of the separate supply pipes is connected to the one ring attachment.
Bevorzugt wird die erste Brennstoffeindüsung von einem ersten Verteilerrohr gespeist und die zweite Brennstoffeindüsung von einem zweiten Verteilerrohr gespeist, wobei das Verteilerrohr in der Drallschaufel integriert ist und wobei die Drallschaufel zwischen dem ersten und zweiten Verteilerrohr geteilt in zwei Schaufelhälften ausgeführt ist. Somit sind die Vertei- lerrohre und die jeweiligen Düsen getrennt mit Brennstoff versorgbar. Dadurch ist eine geregelte Steuerung des Brennstoffflusses möglich. Preferably, the first fuel injection is fed by a first manifold and the second fuel injection is fed by a second manifold, the manifold being integrated in the swirl vane, and wherein the swirl vane between the first and second manifolds is split into two vane halves. Thus, the distribution pipes and the respective nozzles can be supplied separately with fuel. As a result, a controlled control of the fuel flow is possible.
Bevorzugt weisen beide Schaufelhälften stromabwärts einen Passzapfen und stromaufwärts einen Schiebesitz auf. Durch die Passzapfen und den Schiebesitz sind die beiden Schaufelhälften nun thermisch separat dehnbar, wodurch ebenfalls Spannungen reduziert werden. In bevorzugter Ausgestaltung sind der Brennstoffverteilerkanal und das Zufuhrrohr durch einen Steg getrennt, wobei der Steg flexibel ausgeführt ist. Dadurch sind auftretende Spannungen im Steg und in der Brennstoffzufuhranordnung reduzierbar. Der Steg kann dabei aus einem elastischen Werkstoff ge- fertigt sein und/oder aber auch durch eine entsprechende geometrische Gestaltung elastisch wirken und somit Spannungen kompensieren. Dies kann z.B. durch einen gekrümmten oder gewellten Steg bewirkt werden. Bevorzugt ist ein solcher Brenner 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 . Both blade halves preferably have a locating pin downstream and a sliding seat upstream. By the dowel pin and the sliding seat, the two blade halves are now thermally separately expandable, which also stresses are reduced. In a preferred embodiment, the fuel distribution channel and the supply pipe are separated by a web, wherein the web is made flexible. As a result, occurring stresses in the web and in the fuel supply arrangement can be reduced. In this case, the web can be made of an elastic material and / or it can also act elastically by means of a corresponding geometric design and thus compensate for stresses. This can be effected for example by a curved or corrugated web. Preferably, such a burner is provided 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.
Darin zeigen Show in it
FIG 1 einen Brenner in einer stark schematisierten Prinzipskizze, 1 shows a burner in a highly schematized schematic diagram,
FIG 2 eine Prinzipdarstellung einer Drallschaufel mit 2 shows a schematic diagram of a swirl blade with
zwei integrierten Gasstufen,  two integrated gas levels,
FIG 3 eine Prinzipdarstellung einer Brennkammer-Nabe mit zwei integrierten Gasstufen und einem Ölkanal, 3 shows a schematic diagram of a combustion chamber hub with two integrated gas stages and an oil channel,
FIG 4 einen Querschnitt einer erfindungsgemäßen Brennkammer-Nabe mit Ringaufsatz und Drallschaufel, FIG 5 eine Draufsicht auf einen Ringaufsatz mit Drallschaufeln . 4 shows a cross section of a combustion chamber hub according to the invention with ring attachment and swirl blade, FIG 5 is a plan view of a ring attachment with swirl blades.
Nachfolgend wird mit Bezug auf Figur 1, die einen Brenner in einer stark schematisierten Prinzipskizze zeigt, das dem Brenner zugrunde liegende Konzept beschrieben. In the following, the concept underlying the burner will be described with reference to FIG. 1, which shows a burner in a highly schematized schematic diagram.
Der Brenner, der ggf. in Verbindung mit mehreren gleichartigen Brennern beispielsweise in der Brennkammer einer Gasturbinenanlage eingesetzt werden kann, umfasst ein inneres Pi- lotbrennersystem und ein das Pilotbrennersystem konzentrisch umgebendes Hauptbrennersystem. Sowohl Pilotbrennersystem als auch Hauptbrennersystem können wahlweise mit gasförmigen und/oder flüssigen Brennstoffen, wie bspw. Erdgas oder Heizöl, betrieben werden. The burner, which may optionally be used in conjunction with a plurality of similar burners, for example in the combustion chamber of a gas turbine plant, comprises an inner pilot burner system and a main burner system concentrically surrounding the pilot burner system. Both the pilot burner system and the main burner system may optionally be operated with gaseous and / or liquid fuels, such as natural gas or fuel oil.
Das Pilotbrennersystem umfasst einen inneren Ölzufuhrkanal 1, der von einem inneren ringförmigen Gaszufuhrkanal 3 konzentrisch umgeben sein kann. Dieser kann wiederum von einem in- neren Luftzufuhrkanal oder Inertstoffzufuhrkanal 5 konzentrisch umgeben sein. In oder an diesem Luftzufuhrkanal kann zudem ein geeignetes Zündsystem angeordnet sein (in der Figur nicht dargestellt) . Das Pilotbrennersystem weist eine einer Brennkammer 7 zuzuwendende Austrittsöffnung 9 auf, in deren Bereich eine Drallbeschaufelung 11 im Luftzufuhrkanal angeordnet sein kann. Mittels Düsenöffnungen 13 kann Gas aus dem inneren Gaszufuhrkanal 3 im Bereich der Drallbeschaufelung oder stromauf der Drallbeschaufelung in den Luftzufuhrkanal 5 eingedüst werden. Öl aus dem Ölzufuhrkanal kann mittels Öldü- sen 15 stromab der Drallbeschaufelung in die zugeführte Luft bzw. den zugeführten Inertstoff eingedüst werden. The pilot burner system includes an inner oil supply passage 1 which may be concentrically surrounded by an inner annular gas supply passage 3. This, in turn, can be be surrounded concentrically surrounding air supply channel or Inertstoffzufuhrkanal 5. In addition, a suitable ignition system may be arranged in or on this air supply channel (not shown in the figure). The pilot burner system has a combustion chamber 7 zuwerende outlet opening 9, in whose area a twist blading 11 may be arranged in the air supply duct. Gas can be injected from the inner gas supply channel 3 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 5 by means of nozzle openings 13. Oil from the oil supply channel can be injected into the supplied air or the added inert material by means of oil nozzles 15 downstream of the swirl blading.
Das Pilotbrennersystem kann in an sich bekannter Weise mit Öl und/oder Gas als Diffusionsbrenner betrieben werden, in dem der Brennstoff direkt in die Flamme eingedüst wird. Es besteht aber auch die Möglichkeit, das Pilotbrennersystem als Vormischbrenner zu betreiben, in dem der Brennstoff gründlich mit Luft vermischt wird, bevor das Gemisch der Flamme zuge- führt wird. The pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame. However, it is also possible to operate the pilot burner system as a premix burner in which the fuel is thoroughly mixed with air before the mixture is added to the flame.
Das das Pilotbrennersystem umgebende Hauptbrennersystem um- fasst einen radialen äußeren Luftzufuhrkanal 17, auch Ringluftkanal genannt, durch den sich Drallschaufeln 19 einer Drallbeschaufelung erstrecken. Diese Drallschaufeln 19 weisen erste Brennstoffdüsen 21 und zweite Brennstoffdüsen 23 auf, durch die Brenngas in die durch den radialen Luftzufuhrkanal 17 einströmende Luft eingedüst werden kann. In die durch den Luftzufuhrkanal 17 strömende Luft kann mittels Öldüsen 25 zu- dem Öl eingedüst werden. Zwar ist im vorliegenden Ausführungsbeispiel von Öl und Öldüsen die Rede, jedoch soll dies lediglich stellvertretend für geeignete flüssige Brennstoffe und entsprechende Düsen stehen. Die in den Drallschaufeln 19 befindlichen ersten Brennstoffdüsen 21 und zweiten Brennstoffdüsen 23 sowie die Öldüsen 25 werden über eine radial innen liegende Brennstoffzufuhranord- nung, die sogenannte Nabe 27, mit Brennstoff versorgt. Die Drallschaufel 19 und die Nabe 27 weisen eine Brennstoff- Strömungsrichtung auf. In dieser sind erste und zweite ringförmige Brennstoffverteilerkanäle 29 und 31 angeordnet, die die Brennstoffdüsen 21 bzw. 23 mit Gas versorgen. Weiterhin ist in der Nabe 27 ein ringförmiger Ölverteilerkanal 33 angeordnet, der die Öldüsen 25 mit Öl versorgt. Die Brennstoffverteilerkanäle 29, 31 sowie der Ölverteilerkanal 33 werden über Brennstoffzufuhrkanäle 35, 37 bzw. über einen Ölzufuhr- kanal 39 mit dem entsprechenden Brennstoff versorgt. Die Brennstoffzufuhrkanäle 35, 37 versorgen die Brennstoffverteilerkanäle 29, 31 mit Brennstoff. Für den Ölzufuhrkanal 39 liegt ein eigenes Ölzufuhrrohr 43 vor. The main burner system surrounding the pilot burner system comprises a radial outer air supply channel 17, also called an annular air channel, through which swirl blades 19 of a swirl blading extend. These swirl blades 19 have first fuel nozzles 21 and second fuel nozzles 23, through which fuel gas can be injected into the air flowing in through the radial air supply channel 17. Into the air flowing through the air supply channel 17, oil can be injected by means of oil nozzles 25. Although in the present embodiment of oil and oil nozzles, the speech, but this should only be representative of suitable liquid fuels and corresponding nozzles. The first fuel nozzles 21 and second fuel nozzles 23 located in the swirl blades 19 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 27. The Swirl vane 19 and the hub 27 have a fuel flow direction. In this first and second annular fuel distributor channels 29 and 31 are arranged, which supply the fuel nozzles 21 and 23 with gas. Furthermore, in the hub 27, an annular oil distribution channel 33 is arranged, which supplies the oil nozzles 25 with oil. The fuel distributor channels 29, 31 and the oil distribution channel 33 are supplied with fuel via fuel supply channels 35, 37 or via an oil supply channel 39. The fuel supply channels 35, 37 supply the fuel distribution channels 29, 31 with fuel. For the oil supply channel 39 is a separate oil supply pipe 43 before.
Figur 2 zeigt eine Prinzipdarstellung einer Drallschaufel 19 mit zwei integrierten Gasstufen B und D. FIG. 2 shows a schematic representation of a swirl blade 19 with two integrated gas stages B and D.
Die Drallschaufel 19 weist zwei voneinander unabhängige The swirl blade 19 has two independent
Brennstoffverteilerkanäle 29 und 31 auf. Der eine Brennstoffverteilerkanal 29 mit den Auslassdüsen 21 kann beispielsweise zum Eindüsen eines anderen Mediums D als der zweite Brennstoffverteilerkanal 31 über die Auslassdüsen 23 (Medium B) verwendet werden. Vorzugsweise werden beide durch die Brenn- stoffverteilerkanäle 29 und 31 der Drallschaufel 19 einzudü- senden Medien gasförmig sein, z. B. das eine Medium Erdgas und das andere Medium Kohlegas. Ebenso kann über diese Auslassdüsen 21 und/oder 23 bei Bedarf ein Inertstoff wie etwa Wasserdampf eingedüst werden. Fuel distribution channels 29 and 31 on. The one fuel distribution channel 29 with the outlet nozzles 21 can be used, for example, for injecting a different medium D than the second fuel distribution channel 31 via the outlet nozzles 23 (medium B). Preferably, both media to be injected through the fuel distribution channels 29 and 31 of the swirl vane 19 will be gaseous, e.g. As the one medium natural gas and the other medium coal gas. Likewise, an inert material such as water vapor can be injected via these outlet nozzles 21 and / or 23 if necessary.
Figur 3 zeigt eine Brennstoff-Nabe 27 mit den Brennstoffver- teilerkanal 29 und 31 mit Öffnungen, welche den Brennstoff in die Schaufel 19 führt. Die beiden Brennstoffverteilerkanäle 29 und 31 sind im Wesentlichen parallel angeordnet und durch einen Steg 50 getrennt. Erfindungsgemäß wurde nun erkannt, dass für diese doppelteFIG. 3 shows a fuel hub 27 with the fuel distributor channel 29 and 31 with openings, which leads the fuel into the blade 19. The two fuel distribution channels 29 and 31 are arranged substantially parallel and separated by a web 50. According to the invention has now been recognized that for these double
Schaufeleindüsung deshalb eine Realisierung schwierig ist, da keine ausreichende Lebensdauer für den Gasverteiler, das heißt, der Nabe 27 vorhanden ist und somit kein sicherer Ein- satz gewährleistet werden kann. Weiterhin wurde erkannt, dass hohe Temperaturgradienten zwischen den einzelnen Brennstoffpassagen zu hohen Thermospannungen führen, welche die Lebensdauer stark einschränken. Bucket injection therefore a realization is difficult because there is no sufficient service life for the gas distributor, that is, the hub 27 is present and thus no safe can be guaranteed. Furthermore, it was recognized that high temperature gradients between the individual fuel passages lead to high thermal stresses, which severely limit the service life.
Erfindungsgemäß wird nun zumindest einer der Brennstoffverteilerkanäle 29 (bzw. alternativ 31) als Zufuhrrohr 55 ausgebildet (Fig. 4) . Das Zufuhrrohr 55 mündet stromabwärts in ein Verteilerrohr 65 (bzw. alternativ 70). Stromaufwärts ist das Zufuhrrohr 55 mit dem Ringaufsatz 60 (Fig. 5) verbunden. Dabei ist der Ringaufsatz 60, in Strömungsrichtung gesehen, dem Brennstoffverteilerkanal 31 (bzw. alternativ 29) vorgeschaltet. Somit ist quasi der ursprüngliche Brennstoffverteilerkanal 31 (bzw. alternativ 29) parallel zu dem Zufuhrrohr 55. Der Ringaufsatz 60 wird mit einem separaten Rohranschluss 75 versorgt. Der ursprüngliche Brennstoffverteilerkanal 31 (bzw. alternativ 29) wird mit einem weiteren Kanal 80 versorgt. Somit werden die beiden führenden Gaspassagen, nämlich das Zufuhrrohr 55 mit dem Ringaufsatz 60 und der ursprüngliche Brennstoffverteilerkanal 31 (bzw. alternativ 29) erfindungsgemäß räumlich entkoppelt. Der Ringaufsatz 60 wirkt dahingehend, dass er die hohen Spannungen aus der Nabe 27 herauszieht und gleichmäßig über dem Bauteil verteilt. Dadurch ergibt sich eine Entschärfung des Bauraums durch niedrigere Spannungen. Somit wird die Lebensdauer der Brenner-Nabe 27 wesentlich verlängert. Durch den Ringaufsatz 60 wird das ursprüngliche Aero-Design nicht oder nur unwesentlich beein- flusst. Auch können bereits gefertigte Maschinen leicht mit einem solchen Ringaufsatz 60 und einem solchen Zufuhrrohr 55 aufgrund der nun leichteren Fertigung und des nun leichteren Einbaus versehen werden. According to the invention, at least one of the fuel distributor channels 29 (or alternatively 31) is then designed as a feed tube 55 (FIG. 4). The feed tube 55 opens downstream into a manifold 65 (or alternatively 70). Upstream, the feed tube 55 is connected to the ring attachment 60 (Figure 5). Here, the ring attachment 60, seen in the flow direction, the fuel distribution channel 31 (or alternatively 29) upstream. Thus, virtually the original fuel distribution channel 31 (or alternatively 29) is parallel to the supply pipe 55. The ring attachment 60 is supplied with a separate pipe connection 75. The original fuel distribution channel 31 (or alternatively 29) is supplied with another channel 80. Thus, the two leading gas passages, namely the feed tube 55 with the ring attachment 60 and the original fuel distribution channel 31 (or alternatively 29) according to the invention spatially decoupled. The ring attachment 60 acts to pull the high stresses out of the hub 27 and distribute them evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the burner hub 27 is substantially extended. The ring attachment 60 does not or only insignificantly influences the original aero design. Also already manufactured machines can easily be provided with such a ring attachment 60 and such a feed tube 55 due to the now easier production and now easier installation.
Bevorzugt wird eine solche erfindungsgemäße Brenner-Nabe 27 im Zusammenhang mit einer geteilten Drallschaufel 19 einge- setzt. Diese umfasst die erste Brennstoffeindüsung 21, die von einem ersten Verteilerrohr 65 gespeist wird, sowie die zweiten Brennstoffeindüsung 23, welche von einem zweiten Verteilerrohr 70 gespeist wird. Dabei ist das Verteilerrohr 65, 70 in der Drallschaufel 19 integriert. Die geteilte Drallschaufel 19 ist nun zwischen dem ersten und zweiten Verteilerrohr 65 und 70 geteilt in zwei Schaufelhälften 19a, 19b ausgeführt. Hierdurch kann noch verbessert die Spannung aus der Nabe 27 gezogen werden, und gleichmäßig über dem Bauteil verteilt werden. Die Schaufelhälften 19a, 19b weisen zudem stromabwärts einen Passzapfen 90a, 90b und stromaufwärts einen Schiebesitz 85a, 85b auf, der sozusagen in der Nabe 27 selber angebracht wird. Durch die Passzapfen 90a, 90b und den Schiebesitz 85a, 85b sind die beiden Schaufelhälften 19a, 19b nun thermisch separat dehnbar, wodurch ebenfalls Spannungen reduziert werden. Such a burner hub 27 according to the invention is preferably used in conjunction with a divided swirl blade 19. This comprises the first fuel injection 21, which is fed by a first distributor pipe 65, and the second fuel injection 23, which is fed by a second distributor pipe 70. In this case, the manifold 65, 70 integrated in the swirl blade 19. The split swirl vane 19 is now interposed between the first and second manifolds 65 and 70 divided into two vane halves 19a, 19b. As a result, the voltage can be further pulled out of the hub 27, and evenly distributed over the component. The blade halves 19a, 19b also have downstream of a fitting pin 90a, 90b and upstream of a sliding seat 85a, 85b, which is mounted so to speak in the hub 27 itself. By the mating pins 90a, 90b and the sliding seat 85a, 85b, the two blade halves 19a, 19b are now thermally separately expandable, which also stresses are reduced.
Um eine zusätzliche Spannungsreduktion zu erhalten, kann der Steg 50, durch welchen der Brennstoffverteilerkanal 31 (bzw. 29) und das Zufuhrrohr 55 getrennt sind, flexibel ausgeführt sein. Der Steg 50 kann dabei aus einem elastischen Werkstoff gefertigt sein. Zusätzlich oder alternativ kann der Steg 50 aber auch durch eine entsprechende Geometrie elastisch wirken und somit Spannungen kompensieren. Dies kann z.B. durch einen gekrümmten oder gewellten Steg 50 bewirkt werden. In order to obtain an additional voltage reduction, the web 50, by which the fuel distributor channel 31 (or 29) and the feed tube 55 are separated, can be made flexible. The web 50 can be made of an elastic material. Additionally or alternatively, the web 50 can also act elastically by a corresponding geometry and thus compensate for stresses. This can e.g. be effected by a curved or corrugated web 50.

Claims

Patentansprüche claims
1. Brenner mit einer zentralen Brennstoffzufuhranordnung (27), einem die zentrale Brennstoffzufuhranordnung (27) umge- benden Ringluftkanal (17) zur Zufuhr von Verbrennungsluft und in dem Ringluftkanal (17) angeordneten Drallschaufeln (19), welche erste Brennstoffdüsen (21) zum Eindüsen eines im Wesentlichen gasförmigen Brennstoffes in die Verbrennungsluft und zweite Brennstoffdüsen (23) zum Eindüsen eines im Wesent- liehen gasförmigen Brennstoffes in die Verbrennungsluft aufweisen, wobei die ersten Brennstoffdüsen (21) von einer A burner having a central fuel supply arrangement (27), an annular air duct (17) surrounding the central fuel supply arrangement (27) for supplying combustion air and swirl vanes (19) arranged in the annular air duct (17) which inject first fuel nozzles (21) a substantially gaseous fuel into the combustion air and second fuel nozzles (23) for injecting a substantially gaseous fuel in the fuel combustion gas, wherein the first fuel nozzles (21) of a
Brennstoffverteilerzufuhr in der Brennstoffzufuhranordnung (27) gespeist werden und die zweiten Brennstoffdüsen (23) von einem Brennstoffverteilerkanal (31) in der Brennstoffzufuhr- anordnung (27) gespeist werden, wobei der Brenner im Betrieb eine Brennstoff-Strömungsrichtung aufweist, Fuel distributor feed in the fuel supply arrangement (27) are fed and the second fuel nozzles (23) are fed by a fuel distributor channel (31) in the fuel supply arrangement (27), wherein the burner has a fuel flow direction in operation,
d a d u r c h g e k e n n z e i c h n e t, d a s s d a d u r c h e s e n c i n e s, d a s s
die Brennstoffverteilerzufuhr ein Zufuhrrohr (55) umfasst, welches stromabwärts mit der Drallschaufel (19) verbunden ist sowie einen Ringaufsatz (60), wobei das Zufuhrrohr (55) stromaufwärts mit dem Ringaufsatz (60) verbunden ist, wobei der Ringaufsatz (60) in Strömungsrichtung gesehen dem Brennstoffverteilerkanal (31) vorgeschaltet ist. the fuel rail feed comprises a feed tube (55) connected downstream of the swirl vane (19) and a ring cap (60), the feed tube (55) being connected upstream to the ring cap (60), the ring cap (60) in the flow direction seen upstream of the fuel distribution channel (31).
2. Brenner nach Anspruch 1, 2. Burner according to claim 1,
d a d u r c h g e k e n n z e i c h n e t, d a s s d a d u r c h e s e n c i n e s, d a s s
der Ringaufsatz (60) einen separaten Rohranschluss (75) umfasst . the ring attachment (60) comprises a separate pipe connection (75).
3. Brenner nach einem der vorhergehenden Ansprüche, 3. Burner according to one of the preceding claims,
d a d u r c h g e k e n n z e i c h n e t, d a s s d a d u r c h e s e n c i n e s, d a s s
mehrere Drallschaufeln (19) vorgesehen sind, und jede einzelne dieser Drallschaufeln (19) ein separates Zufuhrrohr (55) aufweist, wobei jedes der separaten Zufuhrrohre (55) mit dem einen Ringaufsatz (60) verbunden ist. a plurality of swirl blades (19) are provided, and each of these swirl vanes (19) has a separate supply pipe (55), wherein each of the separate supply pipes (55) is connected to the one ring attachment (60).
4. Brenner nach einem der vorhergehenden Ansprüche, 4. Burner according to one of the preceding claims,
d a d u r c h g e k e n n z e i c h n e t, d a s s die ersten Brennstoffeindüsung (21) von einem ersten Verteilerrohr (65) gespeist und die zweiten Brennstoffeindüsung (23) von einem zweiten Verteilerrohr (70) gespeist wird, wobei das Verteilerrohr (65,70) in der Drallschaufel integriert ist und wobei die Drallschaufel (19) zwischen den ersten und zweiten Verteilerrohr (65) und (70) geteilt in zwei Schaufelhälften (19a, 19b) ausgeführt ist. characterized in that the first fuel injection (21) is fed by a first manifold (65) and the second fuel injection (23) is fed by a second manifold (70), the manifold (65, 70) being integrated in the swirl vane, and wherein the swirl vane (19 ) between the first and second distribution pipes (65) and (70) divided into two blade halves (19a, 19b) is executed.
5. Brenner nach Anspruch 4, 5. Burner according to claim 4,
d a d u r c h g e k e n n z e i c h n e t, d a s s d a d u r c h e s e n c i n e s, d a s s
beide Schaufelhälften (19a, 19b) stromabwärts einen Passzapfen (90a, 90b) aufweisen. both blade halves (19a, 19b) downstream of a fitting pin (90a, 90b) have.
6. Brenner nach Anspruch 5, 6. Burner according to claim 5,
d a d u r c h g e k e n n z e i c h n e t, d a s s d a d u r c h e s e n c i n e s, d a s s
beide Schaufelhälften (19a, 19b) stromaufwärts einen Schiebesitz (85a, 85b) aufweisen. both blade halves (19a, 19b) have upstream a sliding seat (85a, 85b).
7. Brenner nach Anspruch 1, 7. Burner according to claim 1,
d a d u r c h g e k e n n z e i c h n e t, d a s s derd a d u r c h e c e n c i n e, the s
Brennstoffverteilerkanal (31) und das Zufuhrrohr (55) durch einen Steg (50) getrennt sind, wobei der Steg (50) flexibel ausgeführt ist, wodurch auftretende Spannungen im Steg (50) reduzierbar sind. Fuel distribution channel (31) and the feed tube (55) by a web (50) are separated, wherein the web (50) is made flexible, whereby occurring stresses in the web (50) are reducible.
8. Gasturbine mit wenigstens einem Brenner nach einem der vorangehenden Ansprüche. 8. Gas turbine with at least one burner according to one of the preceding claims.
EP10749631.7A 2009-08-26 2010-08-24 Burner, in particular for gas turbines Not-in-force EP2470834B1 (en)

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PCT/EP2010/062284 WO2011023669A1 (en) 2009-08-26 2010-08-24 Burner, in particular for gas turbines

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RU2536465C2 (en) 2014-12-27
RU2012111248A (en) 2013-10-10

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