EP2449310B1 - Burner, especially for gas turbines - Google Patents

Burner, especially for gas turbines Download PDF

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Publication number
EP2449310B1
EP2449310B1 EP10718576.1A EP10718576A EP2449310B1 EP 2449310 B1 EP2449310 B1 EP 2449310B1 EP 10718576 A EP10718576 A EP 10718576A EP 2449310 B1 EP2449310 B1 EP 2449310B1
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EP
European Patent Office
Prior art keywords
gas
gas supply
duct
burner according
burner
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EP10718576.1A
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German (de)
French (fr)
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EP2449310A1 (en
Inventor
Andreas Böttcher
Mariano Cano Wolff
Andre Kluge
Tobias Krieger
Ulrich Wörz
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Siemens AG
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Siemens AG
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Priority to EP10718576.1A priority Critical patent/EP2449310B1/en
Publication of EP2449310A1 publication Critical patent/EP2449310A1/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
    • F23R3/283—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
    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses

Definitions

  • the present invention relates to a burner, and more particularly to a gas turbine combustor having a central fuel supply arrangement.
  • the invention relates to a gas turbine.
  • burners have been developed in recent years that have particularly low emissions of nitrogen oxides (NOx). It is often emphasized that such burners are not only with a fuel, but possibly with different fuels, such as oil and natural gas, either selectively or in combination operable to increase the security of supply and flexibility of operation. Such burners are for example in the EP 0 276 696 B1 described.
  • the in EP 0 276 696 B1 described burner is a hybrid burner for Vormisch plante with gas and / or oil, as it is used in particular for gas turbine plants.
  • the burner comprises a central fuel supply 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 central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with therein a swirl blading with a plurality of blades and nozzle pipes arranged upstream of the blades for premixing with gas.
  • 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.
  • the fuel gas can also be injected into the air duct through nozzle openings arranged in the swirl vanes itself, as described, for example, in US Pat EP 0 580 683 B1 is described.
  • EP 1 614 967 A1 discloses a burner according to the features of the preamble of claim 1.
  • the first object is achieved by a burner according to claim 1, the second object by a gas turbine according to claim 15.
  • the dependent claims contain advantageous embodiments of the invention.
  • a burner according to the invention has a central fuel supply arrangement and an annular air duct surrounding the central fuel supply arrangement for supplying combustion air on.
  • swirl vanes are arranged, which have first gas nozzles for injecting a gaseous fuel into the combustion air and second gas nozzles for injecting a gaseous fuel into the combustion air.
  • the first gas nozzles are fed by a first gas distribution channel in the fuel supply arrangement, the second gas nozzles by a second gas distribution channel in the fuel supply arrangement.
  • the first gas distribution channel and the second gas distribution channel are supplied with fuel gas from a gas supply tube having a first gas supply channel and a second gas supply channel, wherein the first gas supply channel is connected to the first gas distribution channel and the second gas supply channel to the second gas distribution channel.
  • the two gas distribution channels are supplied with fuel instead of two separate gas supply pipes via a single, common gas supply pipe, wherein in the gas supply pipe for each gas distribution channel a separate gas supply channel is present.
  • the contour of the central fuel supply arrangement as it is known for a single gas distribution channel, approximately corresponding to the burner EP 0 580 683 B1 be maintained even in the presence of two gas distribution channels.
  • the gas supply channels can either be arranged coaxially to each other in the gas supply pipe or side by side.
  • the two gas supply channels according to a first embodiment coaxial with each other in the gas supply pipe they can be formed by the gas supply pipe comprises an outer tube and an inner tube, wherein the first gas supply channel is formed by the gap between the outer tube and the inner tube and the second gas supply passage from the interior of the inner tube.
  • the two tubes may have different thermal Strains result. These can be compensated if the inner tube and / or the outer tube has or have an elastic compensation element which enables or permits axial expansion or compression of the inner tube.
  • the inner tube and / or the outer tube may be divided into two axial parts which are interconnected via a bellows. Basically corrugated bellows or bellows come into question. These allow an expansion or contraction of the respective tube and thus a compensation for different thermal expansions.
  • the first gas supply channel has an annular flow cross section and the second gas supply channel has a circular flow cross section.
  • an adapter piece may be provided between the gas supply tube and the gas distribution channels, which converts the annular flow cross section and the circular flow cross section in cross sections with maximum flow areas for the gas flowing into the gas distribution channels.
  • the first gas supply channel and the second gas supply channel may each have a flow cross-section with maximum for the flowing gas flow area at least at their ends facing the gas distribution channels. In this way, it is possible to ensure optimal inflow of the gas supplied via the gas supply channels into the gas distribution channels.
  • the first gas supply channel can be supplied with fuel via a first gas supply connection, while the second gas supply channel is supplied with fuel via a second gas supply connection.
  • a straight connecting line between the first gas supply port and the second gas supply port may include an angle to a straight connecting line between the first gas supply channel and the second gas supply channel, in particular an angle of 90 °.
  • the gas supply ports may each have a circular flow cross-section.
  • the transition section can then convert the circular flow cross sections in cross sections with maximum flow areas for the flowing gas.
  • the gas connections can be designed so that they correspond to the previous standard, possibly with the exception of their dimensions.
  • the gas supply pipe with the juxtaposed gas supply channels can be advantageously designed as a casting, which in particular allows the already described rotation of the straight connecting lines and also can realize a constant wall thickness over the entire component.
  • a gas turbine according to the invention comprises at least one burner according to the invention.
  • the flexibility in operating the gas turbine can be increased because a two-stage gas injection into the air supply channel is possible without significant changes to the aerodynamics of the burner are needed.
  • FIG. 1 shows a burner according to the invention in a highly schematic schematic diagram, which described the concept underlying the burner.
  • the burner according to the invention which can 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 pilot burner system and main burner system can optionally with gaseous and / or liquid fuels, such as, for example, natural gas or fuel oil operated.
  • the pilot burner system includes an inner oil supply passage 1 concentrically surrounded by an inner annular gas supply passage 3. This is in turn surrounded by an inner air supply channel or Inertstoffzubuchkanal 5 concentrically.
  • 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 is arranged in the air supply channel. Gas can be injected from the inner gas supply channel 3 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 5 by means of nozzle openings 13. Oil from the oil supply channel can be injected by means of oil nozzles 15 downstream of the swirl blading into the supplied air or the supplied inert material.
  • the pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame.
  • a diffusion burner in which the fuel is injected directly into the flame.
  • the pilot burner system it is also possible to operate the pilot burner system as a premix burner, in which the fuel is thoroughly mixed with air before the mixture is fed to the flame.
  • the main burner system surrounding the pilot burner system comprises a radial outer air supply channel 17, also called an annular air channel, through which swirl blades 19 of a swirl blading extend.
  • These swirl vanes 19 have first gas nozzles 21 and second gas nozzles 23, through which fuel gas can be injected into the air flowing in through the radial air supply duct 17.
  • air can also be injected by means of oil nozzles 25 oil.
  • the first gas nozzles 21 and second gas nozzles 23 located in the swirl vanes 19 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 27.
  • this first and second annular gas distribution channels 29 and 31 are arranged, which supply the gas nozzles 21 and 23 with gas.
  • an annular oil distribution channel 33 is arranged, which supplies the oil nozzles 25 with oil.
  • the gas distribution channels 29, 31 and the oil distribution channel 33 are supplied via gas supply channels 35, 37 and via an oil supply channel 39 with the appropriate fuel.
  • the gas supply channels 35, 37, which supply the gas distribution channels 29, 31 with fuel, are integrated in a common gas supply pipe 41.
  • For the oil supply channel 39 is a separate oil supply pipe 43 before.
  • the integration of the two gas supply channels 35, 37 in a common gas supply pipe 41 has the advantage that the aerodynamics of the burner with respect to the air flowing into the air supply channels 5, 17 air compared to a burner with only a single gas supply channel and a single set of gas nozzles not changed.
  • the burner according to the invention can therefore replace existing burners in existing combustion systems without the aerodynamics of the combustion system thereby changing.
  • a first concrete embodiment of the burner according to the invention in particular the gas supply pipe 41 with the gas supply channels 35, 37 will be described below with reference to the FIGS. 2 to 5 described.
  • the gas supply channels 35, 37 are arranged coaxially with each other in the gas supply pipe 41.
  • the gas supply channel 37 supplying gas to the second annular gas distribution channel 31 is formed by the lumen of an inner tube 35, whereas that of the first annular gas distribution channel 29 supplying gas supply channel 35 from the cavity between the outer surface of the inner tube 45 and the inner surface of an outer tube 46 is formed.
  • the outer tube 46 forms the outer wall of the gas supply pipe 41.
  • the inner tube 45 is cooled by the gas flowing therethrough and the outer tube 46 is heated by the warm compressor air flowing along, the two tubes 45, 46 experience different thermal expansions.
  • the inner tube 45 is formed in two parts, wherein between the tube parts 45, 45 'an elastic compensation element 47 is arranged.
  • the elastic compensation element is designed as a bellows, which allows an axial displacement of the two tube parts 45, 45 'against each other. Different thermal expansions between the outer tube 46 and the inner tube 45 can thus be compensated.
  • the compensation element can also be arranged on the outer tube 46.
  • the provision of two compensation elements, one on the inner tube 45 and one on the outer tube 46 is also possible. For the compensation element on the outer tube 46, this is analogous with respect to the design of the compensation element on the inner tube 45.
  • an adapter piece 49 is provided, which has the annular flow cross section of the first gas supply channel 35 and the circular flow cross section of the second gas supply channel 37 in flow cross sections with maximum flow areas for the flowing gas transferred. In this way, the flow from the gas supply channels into the respective annular gas distribution channels can be optimized, whereby more uniform heat transfer rates can be achieved and the life and the life prediction of the burner can be improved.
  • the adapter piece 49 is in FIG. 3 shown in a perspective view. It has an approximately semicircular curved edge portion 51 with an outer surface 53, which is adapted in its radius of curvature to the wall of the outer tube 46. In addition, it has a circular projection 55, which can be connected to the inner tube 45.
  • the circular flow cross section and the annular flow cross section are converted into flow cross sections optimized with regard to the creation of maximum flow areas.
  • the optimized flow cross sections which result with the aid of the adapter piece at the outlet of the gas supply pipe 41, are in FIG. 4 shown. This shows the flow openings provided with the corresponding flow cross-sections corresponding inlet openings 57, 59 to the annular gas distribution channels 29, 31st
  • FIG. 5 shows an enlarged section FIG. 2 in which the arrangement of the adapter piece 49 and the connection with the inner tube 45 and the outer tube 46 are shown.
  • the adapter piece 49 is connected by means of welded connections on the one hand to the hub 27 and on the other hand to the inner tube 45 and the outer tube 46. Due to the only part-circular configuration of the adapter piece 49, which is a semicircular configuration in the present embodiment, it is possible first to weld the adapter piece 49 to the hub 27, then to weld the inner tube 45 on the adapter piece 49 and finally over the outer tube 46 and to weld with the adapter piece 49. If the adapter piece 49 would have a completely annular wall element, in particular the dense bonding of the part of the adapter piece 49 forming the inner gas supply channel to the hub 27 would be difficult to accomplish.
  • the referring to the FIGS. 2 to 5 described first specific embodiment of the burner according to the invention has the advantage that has a negative impact on the air flow
  • the radial air supply channel 17 can avoid, since no change in the outer hub geometry or the gas supply pipe 41 needs to be compared to a burner with only one gas distribution channel.
  • the flow cross-sections can be optimally utilized with the aid of the adapter piece, whereby unnecessary pressure losses are avoided.
  • the embodiment according to the first concrete embodiment allows a robust construction, which also allows easy mounting.
  • FIG. 6 shows the hub 27 of the burner according to the invention with a arranged in its center pilot burner 63 and the gas supply pipe 141 in a perspective view.
  • a burner support 65 can be seen, in which there are two connections 67, 69 for the two gas supply ducts 135, 137 located in the gas supply pipe 141.
  • the gas supply pipe 141 of the second specific embodiment is in FIG. 7 shown in a perspective view. It differs from the gas supply pipe 41 of the first concrete embodiment in that the gas supply channels 135, 137 are arranged side by side instead of concentric with each other.
  • the geometry of the gas supply channels 135, 137 is selected such that there are flow cross sections with maximum flow areas at least at the hub-side outlet end 71 of the gas supply tube.
  • the two gas ports for the gas supply pipe 141 are arranged. These are also arranged side by side, but a connecting line A, which connects the centers of the two gas ports 67, 69 with each other by 90 ° with respect to a connecting line B, the centers of the gas supply channels 135, 137 at the hub end of the gas supply pipe 141 connects to each other Turned 90 °.
  • the twisting can also be done by other angles than 90 °, if another arrangement of the gas ports 67th , 69 in the burner carrier 65 is desired.
  • the gas supply pipe 141 of the second concrete embodiment of the burner according to the invention can be designed in particular as a cast construction. In such, in particular with a twisting of the channels in the pipe by 90 °, a constant wall thickness over the entire component can be achieved.
  • the design of the gas supply pipe 141 according to the second specific embodiment offers the particular advantage that the distribution of the gas supply channels in two separate gas connections between the burner carrier and the hub takes place. This simplifies the assembly of the burner. The burner carrier flange is then only provided with two fitting holes.
  • the tube construction hardly changes the aerodynamics compared to a burner with only one gas distribution channel in the hub. Since the transition section is located in the vicinity of the burner support - and thus away from the air ducts of the pilot burner and the main burner - this change in the gas supply pipe leads to a gas supply pipe with only one gas supply channel not to a significant change in the aerodynamics of the burner.

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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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Combustion Of Fluid Fuel (AREA)

Description

Die vorliegende Erfindung betrifft einen Brenner und insbesondere einen Gasturbinenbrenner mit einer zentralen Brennstoffzufuhranordnung. Daneben betrifft die Erfindung eine Gasturbine.The present invention relates to a burner, and more particularly to a gas turbine combustor having a central fuel supply arrangement. In addition, the invention relates to a gas turbine.

Im Hinblick auf die weltweiten Bemühungen zur Senkung des Schadstoffausstoßes von Befeuerungsanlagen, insbesondere bei Gasturbinen, wurden in den letzten Jahren Brenner entwickelt, die besonders geringe Ausstöße an Stickoxiden (NOx) aufweisen. Dabei wird vielfach Wert darauf gelegt, dass solche Brenner jeweils nicht nur mit einem Brennstoff, sondern möglichst mit verschiedenen Brennstoffen, beispielsweise Öl und Erdgas wahlweise oder in Kombination betreibbar sind, um die Versorgungssicherheit und Flexibilität des Betriebs zu erhöhen. Solche Brenner sind beispielsweise in der EP 0 276 696 B1 beschrieben.In view of the global efforts to reduce pollutant emissions from firing systems, particularly in gas turbines, burners have been developed in recent years that have particularly low emissions of nitrogen oxides (NOx). It is often emphasized that such burners are not only with a fuel, but possibly with different fuels, such as oil and natural gas, either selectively or in combination operable to increase the security of supply and flexibility of operation. Such burners are for example in the EP 0 276 696 B1 described.

Der in EP 0 276 696 B1 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 aufweist. Zusätzlich sind in der Brennstoffzufuhranordnung Einlassdüsen für Öl im Bereich der Drallbeschaufelung vorhanden, die eine Vormischung des Hauptluftstroms mit Öl ermöglichen.The in EP 0 276 696 B1 described burner is a hybrid burner for Vormischbetrieb 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 therein a swirl blading with a plurality of blades and nozzle pipes arranged upstream of the blades for premixing with gas. 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.

Statt wie in EP 0 276 696 B1 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 B1 beschrieben ist.Instead of like in EP 0 276 696 B1 By means of nozzle pipes 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 itself, as described, for example, in US Pat EP 0 580 683 B1 is described.

Um die Kontrolle der Emissionen und der Verbrennungsstabilität zukünftig noch zu erhöhen, soll zusätzlich zu einer Gaseindüsung durch die Schaufel wie in EP 0 580 683 B1 eine weitere Gaseindüsung durch die Schaufel genutzt werden. Diese zusätzliche Gaseindüsung 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 Brennstoffzuführeinrichtung des Brenners eingebracht werden. Eine Schwierigkeit besteht nun darin, diesen zusätzlichen Gaskanal mit Brennstoff zu versorgen, ohne dass dabei das bisherige Brennerdesign aerodynamisch verändert wird. Dies gilt vor allem für die Außenkontur der zentralen Brennstoffzufuhranordnung bzw. der Drallschaufeln, welche den Strömungskanal für die zugeführte Verbrennungsluft bilden.In order to increase the control of emissions and combustion stability in the future, in addition to a gas injection through the blade as in EP 0 580 683 B1 another gas injection can be used by the blade. This additional gas injection should be controllable separately from the main gas stage, ie, 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. One difficulty now is to provide this additional gas channel with fuel, without the previous burner design is changed aerodynamically. This is especially true for the outer contour of the central fuel supply arrangement or the swirl blades, which form the flow channel for the supplied combustion air.

EP 1 614 967 A1 offenbart einen Brenner nach den Merkmalen des Oberbegriffs des Anspruchs 1. EP 1 614 967 A1 discloses a burner according to the features of the preamble of claim 1.

Aufgabe der vorliegenden Erfindung ist es daher, einen Brenner, insbesondere einen Gasturbinenbrenner, zur Verfügung zu stellen, der die Zufuhr von Brenngas zu einem zweiten Gaskanal ermöglicht, ohne dass die Außenkontur der zentralen Brennstoffzufuhranordnung wesentlich verändert wird.It is therefore an object of the present invention to provide a burner, in particular a gas turbine burner, which makes it possible to supply fuel gas to a second gas channel without substantially changing the outer contour of the central fuel supply arrangement.

Es ist eine zweite Aufgabe der vorliegenden Erfindung, eine vorteilhafte Gasturbine zur Verfügung zu stellen.It is a second object of the present invention to provide an advantageous gas turbine.

Die erste Aufgabe wird durch einen Brenner nach Anspruch 1 gelöst, die zweite Aufgabe durch eine Gasturbine nach Anspruch 15. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.The first object is achieved by a burner according to claim 1, the second object by a gas turbine according to claim 15. The dependent claims contain advantageous embodiments of the invention.

Ein erfindungsgemäßer Brenner weist eine zentrale Brennstoffzufuhranordnung und einen die zentrale Brennstoffzufuhranordnung umgebenden Ringluftkanal zur Zufuhr von Verbrennungsluft auf. In dem Ringluftkanal sind Drallschaufeln angeordnet, welche erste Gasdüsen zum Eindüsen eines gasförmigen Brennstoffs in die Verbrennungsluft und zweite Gasdüsen zum Eindüsen eines gasförmigen Brennstoffs in die Verbrennungsluft aufweisen. Die ersten Gasdüsen werden von einem ersten Gasverteilerkanal in der Brennstoffzufuhranordnung gespeist, die zweiten Gasdüsen von einem zweiten Gasverteilerkanal in der Brennstoffzufuhranordnung. Der erste Gasverteilerkanal und der zweite Gasverteilerkanal werden von einem Gaszufuhrrohr mit Brenngas versorgt, welches einen ersten Gaszufuhrkanal und einen zweiten Gaszufuhrkanal aufweist, wobei der erste Gaszufuhrkanal mit dem ersten Gasverteilerkanal verbunden ist und der zweite Gaszufuhrkanal mit dem zweiten Gasverteilerkanal.A burner according to the invention has a central fuel supply arrangement and an annular air duct surrounding the central fuel supply arrangement for supplying combustion air on. In the annular air duct swirl vanes are arranged, which have first gas nozzles for injecting a gaseous fuel into the combustion air and second gas nozzles for injecting a gaseous fuel into the combustion air. The first gas nozzles are fed by a first gas distribution channel in the fuel supply arrangement, the second gas nozzles by a second gas distribution channel in the fuel supply arrangement. The first gas distribution channel and the second gas distribution channel are supplied with fuel gas from a gas supply tube having a first gas supply channel and a second gas supply channel, wherein the first gas supply channel is connected to the first gas distribution channel and the second gas supply channel to the second gas distribution channel.

Erfindungsgemäß werden also die beiden Gasverteilerkanäle statt durch zwei getrennte Gaszufuhrrohre über ein einziges, beiden Kanälen gemeinsames Gaszufuhrrohr mit Brennstoff versorgt, wobei in dem Gaszufuhrrohr für jeden Gasverteilerkanal ein eigener Gaszufuhrkanal vorhanden ist. Dadurch kann die Kontur der zentralen Brennstoffzufuhranordnung, wie sie für einen einzigen Gasverteilerkanal bekannt ist, etwa entsprechend dem Brenner aus EP 0 580 683 B1 , auch bei Vorhandensein von zwei Gasverteilerkanälen beibehalten werden. Die Gaszufuhrkanäle können entweder koaxial zueinander im Gaszufuhrrohr angeordnet sein oder nebeneinander.According to the invention, therefore, the two gas distribution channels are supplied with fuel instead of two separate gas supply pipes via a single, common gas supply pipe, wherein in the gas supply pipe for each gas distribution channel a separate gas supply channel is present. Thereby, the contour of the central fuel supply arrangement, as it is known for a single gas distribution channel, approximately corresponding to the burner EP 0 580 683 B1 be maintained even in the presence of two gas distribution channels. The gas supply channels can either be arranged coaxially to each other in the gas supply pipe or side by side.

Falls die beiden Gaszufuhrkanäle gemäß einer ersten Ausgestaltung koaxial zueinander im Gaszufuhrrohr verlaufen, können diese dadurch gebildet werden, dass das Gaszufuhrrohr ein äußeres Rohr und ein inneres Rohr umfasst, wobei der erste Gaszufuhrkanal von dem Zwischenraum zwischen dem äußeren Rohr und dem inneren Rohr gebildet ist und der zweite Gaszufuhrkanal von dem Innenraum des inneren Rohres.If the two gas supply channels according to a first embodiment coaxial with each other in the gas supply pipe, they can be formed by the gas supply pipe comprises an outer tube and an inner tube, wherein the first gas supply channel is formed by the gap between the outer tube and the inner tube and the second gas supply passage from the interior of the inner tube.

Da das innere Rohr durch den strömenden Brennstoff gekühlt wird und das äußere Rohr durch Verdichterluft erwärmt wird, können sich bei den beiden Rohren unterschiedliche thermische Dehnungen ergeben. Diese können ausgeglichen werden, wenn das innere Rohr und/oder das äußere Rohr ein elastisches Kompensationselement aufweist bzw. aufweisen, das bzw. die eine axiale Ausdehnung oder Kompression des inneren Rohres ermöglicht bzw. ermöglichen. Insbesondere kann hierbei das innere Rohr und/oder das äußere Rohr in zwei axiale Teile aufgeteilt sein, die über einen Balg miteinander verbunden sind. Hierbei kommen grundsätzlich Wellbälge oder Faltenbälge in Frage. Diese erlauben eine Ausdehnung oder Kontraktion des jeweiligen Rohres und somit einen Ausgleich für unterschiedliche thermische Dehnungen.Since the inner tube is cooled by the flowing fuel and the outer tube is heated by compressor air, the two tubes may have different thermal Strains result. These can be compensated if the inner tube and / or the outer tube has or have an elastic compensation element which enables or permits axial expansion or compression of the inner tube. In particular, in this case, the inner tube and / or the outer tube may be divided into two axial parts which are interconnected via a bellows. Basically corrugated bellows or bellows come into question. These allow an expansion or contraction of the respective tube and thus a compensation for different thermal expansions.

In der beschriebenen Ausgestaltung des Gaszuführrohres weist der erste Gaszufuhrkanal einen ringförmigen Strömungsquerschnitt auf und der zweite Gaszufuhrkanal einen kreisförmigen Strömungsquerschnitt. Um das Strömen des Gases von den Gaszufuhrkanälen in die Gasverteilerkanäle zu optimieren, kann zwischen dem Gaszufuhrrohr und den Gasverteilerkanälen ein Adapterstück vorhanden sein, welches den ringförmigen Strömungsquerschnitt und den kreisförmigen Strömungsquerschnitt in Querschnitte mit für das in die Gasverteilerkanäle strömende Gas maximalen Strömungsflächen überführt. Wenn das Adapterstück einen Teil des äußeren Umfangs des äußeren Rohres bildet und das äußere Rohr eine entsprechende Aussparung in der Umfangswand aufweist, kann der Adapter komplett mit dem inneren Rohr und dem äußeren Rohr verschweißt werden, so dass die Gaskanäle gegeneinander abgedichtet sind.In the described embodiment of the gas supply pipe, the first gas supply channel has an annular flow cross section and the second gas supply channel has a circular flow cross section. In order to optimize the flow of the gas from the gas supply channels into the gas distribution channels, an adapter piece may be provided between the gas supply tube and the gas distribution channels, which converts the annular flow cross section and the circular flow cross section in cross sections with maximum flow areas for the gas flowing into the gas distribution channels. When the adapter piece forms part of the outer circumference of the outer tube and the outer tube has a corresponding recess in the peripheral wall, the adapter can be completely welded to the inner tube and the outer tube, so that the gas channels are sealed against each other.

Wenn der erste Gaszufuhrkanal und der zweite Gaszufuhrkanal gemäß einer zweiten Ausgestaltung des Gaszufuhrrohres nebeneinander in dem Gaszufuhrrohr verlaufen, können der erste Gaszufuhrkanal und der zweite Gaszufuhrkanal zumindest an ihren den Gasverteilerkanälen zugewandten Enden jeweils einen Strömungsquerschnitt mit für das strömende Gas maximaler Strömungsfläche aufweisen. Hierdurch kann für ein optimales Einströmen des über die Gaszufuhrkanäle zugeführten Gases in die Gasverteilerkanäle gesorgt werden.When the first gas supply channel and the second gas supply channel according to a second embodiment of the gas supply pipe run side by side in the gas supply pipe, the first gas supply channel and the second gas supply channel may each have a flow cross-section with maximum for the flowing gas flow area at least at their ends facing the gas distribution channels. In this way, it is possible to ensure optimal inflow of the gas supplied via the gas supply channels into the gas distribution channels.

In der Ausgestaltung mit zwei nebeneinander verlaufenden Gaszufuhrkanälen kann der erste Gaszufuhrkanal über einen ersten Gaszufuhranschluss mit Brennstoff versorgt werden, während der zweite Gaszufuhrkanal über einen zweiten Gaszufuhranschluss mit Brennstoff versorgt wird. Diese sind dann einander benachbart angeordnet und mittels eines Übergangsabschnittes mit den Gaszufuhrkanälen verbunden. Hierbei kann insbesondere eine gerade Verbindungslinie zwischen dem ersten Gaszufuhranschluss und dem zweiten Gaszufuhranschluss einen Winkel zu einer geraden Verbindungslinie zwischen dem ersten Gaszufuhrkanal und dem zweiten Gaszufuhrkanal einschließen, insbesondere einen Winkel von 90°.In the embodiment with two adjacent gas supply channels, the first gas supply channel can be supplied with fuel via a first gas supply connection, while the second gas supply channel is supplied with fuel via a second gas supply connection. These are then arranged adjacent to each other and connected by means of a transition section with the gas supply channels. In this case, in particular a straight connecting line between the first gas supply port and the second gas supply port may include an angle to a straight connecting line between the first gas supply channel and the second gas supply channel, in particular an angle of 90 °.

Zudem können die Gaszufuhranschlüsse jeweils einen kreisförmigen Strömungsquerschnitt aufweisen. Der Übergangsabschnitt kann dann auch die kreisförmigen Strömungsquerschnitte in Querschnitte mit für das strömende Gas maximalen Strömungsflächen überführen. Auf diese Weise können die Gasanschlüsse so ausgestaltet werden, dass sie dem bisherigen Standard, eventuell mit Ausnahme ihrer Abmessungen, entsprechen.In addition, the gas supply ports may each have a circular flow cross-section. The transition section can then convert the circular flow cross sections in cross sections with maximum flow areas for the flowing gas. In this way, the gas connections can be designed so that they correspond to the previous standard, possibly with the exception of their dimensions.

Das Gaszufuhrrohr mit den nebeneinander angeordneten Gaszufuhrkanälen kann vorteilhafterweise als Gussteil ausgestaltet sein, was insbesondere die bereits beschriebene Verdrehung der geraden Verbindungslinien ermöglicht und zudem eine konstante Wandstärke über das gesamte Bauteil realisieren lässt.The gas supply pipe with the juxtaposed gas supply channels can be advantageously designed as a casting, which in particular allows the already described rotation of the straight connecting lines and also can realize a constant wall thickness over the entire component.

Eine erfindungsgemäße Gasturbine umfasst wenigstens einen erfindungsgemäßen Brenner. Mit dem erfindungsgemäßen Brenner kann die Flexibilität beim Betreiben der Gasturbine erhöht werden, da eine zweistufige Gaseindüsung in den Luftzufuhrkanal möglich wird, ohne dass wesentliche Änderungen an der Aerodynamik des Brenners nötig sind.A gas turbine according to the invention comprises at least one burner according to the invention. With the burner according to the invention, the flexibility in operating the gas turbine can be increased because a two-stage gas injection into the air supply channel is possible without significant changes to the aerodynamics of the burner are needed.

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 den erfindungsgemäßen Brenner in einer stark schematisierten Prinzipskizze.
Figur 2
zeigt einen Ausschnitt aus einem ersten Ausführungsbeispiel für den erfindungsgemäßen Brenner in einer teilgeschnittenen perspektivischen Ansicht.
Figur 3
zeigt ein im ersten Ausführungsbeispiel für den erfindungsgemäßen Brenner zur Anwendung kommendes Adapterstück.
Figur 4
zeigt Strömungsquerschnitte des ersten Ausführungsbeispieles.
Figur 5
zeigt ein Detail des ersten Ausführungsbeispieles.
Figur 6
zeigt ein zweites Ausführungsbeispiel für den erfindungsgemäßen Brenner in einer perspektivischen Ansicht.
Figur 7
zeigt ein Gaszufuhrrohr des zweiten Ausführungsbeispiels in einer perspektivischen Ansicht.
Figur 8
zeigt die Gasanschlüsse des Gaszufuhrrohrs aus Figur 7 in einer perspektivischen Ansicht.
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 the burner according to the invention in a highly schematic schematic diagram.
FIG. 2
shows a section of a first embodiment of the burner according to the invention in a partially cutaway perspective view.
FIG. 3
shows an adapter used in the first embodiment for the burner according to the invention for use.
FIG. 4
shows flow cross sections of the first embodiment.
FIG. 5
shows a detail of the first embodiment.
FIG. 6
shows a second embodiment of the burner according to the invention in a perspective view.
FIG. 7
shows a gas supply pipe of the second embodiment in a perspective view.
FIG. 8
shows the gas connections of the gas supply pipe of Figure 7 in a perspective view.

Nachfolgend wird mit Bezug auf Figur 1, die einen erfindungsgemäßen Brenner in einer stark schematisierten Prinzipskizze zeigt, das dem Brenner zugrunde liegende Konzept beschrieben.Hereinafter, with reference to FIG. 1 , which shows a burner according to the invention in a highly schematic schematic diagram, which described the concept underlying the burner.

Der erfindungsgemäße Brenner, der ggf. in Verbindung mit mehreren gleichartigen Brennern beispielsweise in der Brennkammer einer Gasturbinenanlage eingesetzt werden kann, umfasst ein inneres Pilotbrennersystem und ein das Pilotbrennersystem konzentrisch umgebendes Hauptbrennersystem. Sowohl Pilotbrennersystem als auch Hauptbrennersystem können wahlweise mit gasförmigen und/oder flüssigen Brennstoffen, wie bspw. Erdgas oder Heizöl, betrieben werden.The burner according to the invention, which can 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 pilot burner system and main burner system can optionally with gaseous and / or liquid fuels, such as, for example, natural gas or fuel oil operated.

Das Pilotbrennersystem umfasst einen inneren Ölzufuhrkanal 1, der von einem inneren ringförmigen Gaszufuhrkanal 3 konzentrisch umgeben ist. Dieser ist wiederum von einem inneren Luftzufuhrkanal oder Inertstoffzufuhrkanal 5 konzentrisch umgeben. 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 ist. Mittels Düsenöffnungen 13 kann Gas aus dem inneren Gaszufuhrkanal 3 im Bereich der Drallbeschaufelung oder stromauf der Drallbeschaufelung in den Luftzufuhrkanal 5 eingedüst werden. Öl aus dem Ölzufuhrkanal kann mittels Öldüsen 15 stromab der Drallbeschaufelung in die zugeführte Luft bzw. den zugeführten Inertstoff eingedüst werden.The pilot burner system includes an inner oil supply passage 1 concentrically surrounded by an inner annular gas supply passage 3. This is in turn surrounded by an inner air supply channel or Inertstoffzufuhrkanal 5 concentrically. 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 is arranged in the air supply channel. Gas can be injected from the inner gas supply channel 3 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 5 by means of nozzle openings 13. Oil from the oil supply channel can be injected by means of oil nozzles 15 downstream of the swirl blading into the supplied air or the supplied inert material.

Das Pilotbrennersystem kann in an sich bekannter Weise mit Öl und/oder Gas als Diffusionsbrenner betrieben werden, in dem der Brennstoff direkt in die Flamme eingedüst wird. Es besteht aber auch die Möglichkeit, das Pilotbrennersystem als Vormischbrenner zu betreiben, in dem der Brennstoff gründlich mit Luft vermischt wird, bevor das Gemisch der Flamme zugeführt wird.The pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame. However, it is also possible to operate the pilot burner system as a premix burner, in which the fuel is thoroughly mixed with air before the mixture is fed to the flame.

Das das Pilotbrennersystem umgebende Hauptbrennersystem umfasst einen radialen äußeren Luftzufuhrkanal 17, auch Ringluftkanal genannt, durch den sich Drallschaufeln 19 einer Drallbeschaufelung erstrecken. Diese Drallschaufeln 19 weisen erste Gasdüsen 21 und zweite Gasdüsen 23 auf, durch die Brenngas in die durch den radialen Luftzufuhrkanal 17 einströmende Luft eingedüst werden kann. In die durch den Luftzufuhrkanal 17 strömende Luft kann mittels Öldüsen 25 zudem Öl eingedüst werden. Zwar ist im vorliegenden Ausführungsbeispiel von Öl und Öldüsen die Rede, jedoch soll dies lediglich stellvertretend für geeignete flüssige Brennstoffe und entsprechende Düsen stehen.The main burner system surrounding the pilot burner system comprises a radial outer air supply channel 17, also called an annular air channel, through which swirl blades 19 of a swirl blading extend. These swirl vanes 19 have first gas nozzles 21 and second gas nozzles 23, through which fuel gas can be injected into the air flowing in through the radial air supply duct 17. In the air flowing through the air supply channel 17 air can also be injected by means of oil nozzles 25 oil. Although in the present embodiment of oil and oil nozzles talk, but this is only represent representative of suitable liquid fuels and corresponding nozzles.

Die in den Drallschaufeln 19 befindlichen ersten Gasdüsen 21 und zweiten Gasdüsen 23 sowie die Öldüsen 25 werden über eine radial innen liegende Brennstoffzufuhranordnung, die sogenannte Nabe 27, mit Brennstoff versorgt. In dieser sind erste und zweite ringförmige Gasverteilerkanäle 29 und 31 angeordnet, die die Gasdüsen 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 Gasverteilerkanäle 29, 31 sowie der Ölverteilerkanal 33 werden über Gaszufuhrkanäle 35, 37 bzw. über einen Ölzufuhrkanal 39 mit dem entsprechenden Brennstoff versorgt. Die Gaszufuhrkanäle 35, 37, welche die Gasverteilerkanäle 29, 31 mit Brennstoff versorgen, sind in ein gemeinsames Gaszufuhrrohr 41 integriert. Für den Ölzufuhrkanal 39 liegt ein eigenes Ölzufuhrrohr 43 vor.The first gas nozzles 21 and second gas nozzles 23 located in the swirl vanes 19 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 27. In this first and second annular gas distribution channels 29 and 31 are arranged, which supply the gas 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 gas distribution channels 29, 31 and the oil distribution channel 33 are supplied via gas supply channels 35, 37 and via an oil supply channel 39 with the appropriate fuel. The gas supply channels 35, 37, which supply the gas distribution channels 29, 31 with fuel, are integrated in a common gas supply pipe 41. For the oil supply channel 39 is a separate oil supply pipe 43 before.

Die Integration der beiden Gaszufuhrkanäle 35, 37 in ein gemeinsames Gaszufuhrrohr 41 hat dabei den Vorteil, dass die Aerodynamik des Brenners im Hinblick auf die in die Luftzufuhrkanäle 5, 17 einströmenden Luft im Vergleich zu einem Brenner mit lediglich einem einzigen Gaszufuhrkanal und einem einzigen Satz Gasdüsen nicht verändert wird. Der erfindungsgemäße Brenner kann daher in bestehenden Verbrennungssystemen an die Stelle bisheriger Brenner treten, ohne dass sich dadurch die Aerodynamik des Verbrennungssystems ändert.The integration of the two gas supply channels 35, 37 in a common gas supply pipe 41 has the advantage that the aerodynamics of the burner with respect to the air flowing into the air supply channels 5, 17 air compared to a burner with only a single gas supply channel and a single set of gas nozzles not changed. The burner according to the invention can therefore replace existing burners in existing combustion systems without the aerodynamics of the combustion system thereby changing.

Eine erste konkrete Ausgestaltung des erfindungsgemäßen Brenners, insbesondere des Gaszufuhrrohres 41 mit den Gaszufuhrkanälen 35, 37 wird nachfolgend mit Bezug auf die Figuren 2 bis 5 beschrieben. In diesem Ausführungsbeispiel für den erfindungsgemäßen Brenner sind die Gaszufuhrkanäle 35, 37 koaxial zueinander im Gaszufuhrrohr 41 angeordnet. Der den zweiten ringförmig Gasverteilerkanal 31 mit Gas versorgende Gaszufuhrkanal 37 ist vom Lumen eines inneren Rohres 35 gebildet, wohingegen der den ersten ringförmigen Gasverteilerkanal 29 versorgende Gaszufuhrkanal 35 vom Hohlraum zwischen der Außenfläche des inneren Rohres 45 und der Innenfläche eines äußeren Rohres 46 gebildet ist. Das äußere Rohr 46 bildet dabei die Außenwand des Gaszufuhrrohres 41.A first concrete embodiment of the burner according to the invention, in particular the gas supply pipe 41 with the gas supply channels 35, 37 will be described below with reference to the FIGS. 2 to 5 described. In this embodiment of the burner according to the invention, the gas supply channels 35, 37 are arranged coaxially with each other in the gas supply pipe 41. The gas supply channel 37 supplying gas to the second annular gas distribution channel 31 is formed by the lumen of an inner tube 35, whereas that of the first annular gas distribution channel 29 supplying gas supply channel 35 from the cavity between the outer surface of the inner tube 45 and the inner surface of an outer tube 46 is formed. The outer tube 46 forms the outer wall of the gas supply pipe 41.

Da das innere Rohr 45 durch das hindurchströmende Gas gekühlt wird und das äußere Rohr 46 durch die entlang strömende warme Verdichterluft erwärmt wird, erfahren die beiden Rohre 45, 46 unterschiedliche thermische Ausdehnungen. Um diese auszugleichen, ist das innere Rohr 45 zweiteilig ausgebildet, wobei zwischen den Rohrteilen 45, 45' ein elastisches Kompensationselement 47 angeordnet ist. Im vorliegenden Ausführungsbeispiel ist das elastische Kompensationselement als Wellbalg ausgebildet, der eine axiale Verschiebung der beiden Rohrteile 45, 45' gegeneinander ermöglicht. Unterschiedliche thermische Dehnungen zwischen dem äußeren Rohr 46 und dem inneren Rohr 45 können so ausgeglichen werden. Statt wie im vorliegenden Ausführungsbeispiel am inneren Rohr 45 kann das Kompensationselement auch am äußeren Rohr 46 angeordnet sein. Auch das Vorsehen von zwei Kompensationselementen, eines am inneren Rohr 45 und eines am äußeren Rohr 46, ist möglich. Für das Kompensationselement am äußeren Rohr 46 gilt das im Hinblick auf die Ausgestaltung des Kompensationselementes am inneren Rohr 45 Ausgeführte analog.Since the inner tube 45 is cooled by the gas flowing therethrough and the outer tube 46 is heated by the warm compressor air flowing along, the two tubes 45, 46 experience different thermal expansions. To compensate for this, the inner tube 45 is formed in two parts, wherein between the tube parts 45, 45 'an elastic compensation element 47 is arranged. In the present embodiment, the elastic compensation element is designed as a bellows, which allows an axial displacement of the two tube parts 45, 45 'against each other. Different thermal expansions between the outer tube 46 and the inner tube 45 can thus be compensated. Instead of the inner tube 45 as in the present embodiment, the compensation element can also be arranged on the outer tube 46. The provision of two compensation elements, one on the inner tube 45 and one on the outer tube 46 is also possible. For the compensation element on the outer tube 46, this is analogous with respect to the design of the compensation element on the inner tube 45.

Um den Übergang von den Gaszufuhrkanälen 35, 37 zu den ringförmigen Gasverteilerkanälen 29, 31 zu optimieren, ist ein Adapterstück 49 vorhanden, welches den ringförmigen Strömungsquerschnitt des ersten Gaszufuhrkanals 35 und den kreisförmigen Strömungsquerschnitt des zweiten Gaszufuhrkanals 37 in Strömungsquerschnitte mit für das strömende Gas maximalen Strömungsflächen überführt. Auf diese Weise kann die Strömung aus den Gaszufuhrkanälen in die jeweiligen ringförmigen Gasverteilerkanäle optimiert werden, wodurch gleichmäßigere Wärmeübergangszahlen erreichbar sind und die Lebensdauer sowie die Lebensdauervoraussage des Brenners verbessert werden kann.In order to optimize the transition from the gas supply channels 35, 37 to the annular gas distribution channels 29, 31, an adapter piece 49 is provided, which has the annular flow cross section of the first gas supply channel 35 and the circular flow cross section of the second gas supply channel 37 in flow cross sections with maximum flow areas for the flowing gas transferred. In this way, the flow from the gas supply channels into the respective annular gas distribution channels can be optimized, whereby more uniform heat transfer rates can be achieved and the life and the life prediction of the burner can be improved.

Das Adapterstück 49 ist in Figur 3 in einer perspektivischen Darstellung gezeigt. Es weist einen in etwa halbkreisförmig gebogenen Randabschnitt 51 mit einer Außenfläche 53 auf, der in seinem Krümmungsradius an die Wand des äußeren Rohres 46 angepasst ist. Zudem weißt es einen kreisförmigen Ansatz 55 auf, der mit dem Innenrohr 45 verbunden werden kann. Im Inneren des Adapterstücks 49 werden der kreisförmige Strömungsquerschnitt und der ringförmige Strömungsquerschnitt in im Hinblick auf das Schaffen maximaler Strömungsflächen optimierte Strömungsquerschnitte umgewandelt. Die optimierten Strömungsquerschnitte, die sich mit Hilfe des Adapterstücks am Ausgang des Gaszufuhrrohres 41 ergeben, sind in Figur 4 dargestellt. Diese zeigt die mit den maximalen Strömungsflächen entsprechenden Strömungsquerschnitten versehenen Eingangsöffnungen 57, 59 zu den ringförmigen Gasverteilerkanälen 29, 31.The adapter piece 49 is in FIG. 3 shown in a perspective view. It has an approximately semicircular curved edge portion 51 with an outer surface 53, which is adapted in its radius of curvature to the wall of the outer tube 46. In addition, it has a circular projection 55, which can be connected to the inner tube 45. In the interior of the adapter piece 49, the circular flow cross section and the annular flow cross section are converted into flow cross sections optimized with regard to the creation of maximum flow areas. The optimized flow cross sections, which result with the aid of the adapter piece at the outlet of the gas supply pipe 41, are in FIG. 4 shown. This shows the flow openings provided with the corresponding flow cross-sections corresponding inlet openings 57, 59 to the annular gas distribution channels 29, 31st

Figur 5 zeigt einen vergrößerten Ausschnitt aus Figur 2, in dem die Anordnung des Adapterstücks 49 und die Verbindung mit dem inneren Rohr 45 und dem äußeren Rohr 46 dargestellt sind. Das Adapterstück 49 ist mittels Schweißverbindungen einerseits mit der Nabe 27 und andererseits mit dem inneren Rohr 45 sowie dem äußeren Rohr 46 verbunden. Aufgrund der lediglich teilkreisförmigen Ausgestaltung des Adapterstücks 49, die im vorliegenden Ausführungsbeispiel eine halbkreisförmige Ausgestaltung ist, wird es möglich, zuerst das Adapterstück 49 mit der Nabe 27 zu verschweißen, anschließend das innere Rohr 45 am Adapterstück 49 anzuschweißen und schließlich das äußere Rohr 46 überzustülpen und mit dem Adapterstück 49 zu verschweißen. Wenn das Adapterstück 49 ein vollständig ringförmiges Wandelement aufweisen würde, wäre insbesondere die dichte Verweißung des den inneren Gaszuführkanal bildenden Teils des Adapterstücks 49 an der Nabe 27 nur schwer zu bewerkstelligen. FIG. 5 shows an enlarged section FIG. 2 in which the arrangement of the adapter piece 49 and the connection with the inner tube 45 and the outer tube 46 are shown. The adapter piece 49 is connected by means of welded connections on the one hand to the hub 27 and on the other hand to the inner tube 45 and the outer tube 46. Due to the only part-circular configuration of the adapter piece 49, which is a semicircular configuration in the present embodiment, it is possible first to weld the adapter piece 49 to the hub 27, then to weld the inner tube 45 on the adapter piece 49 and finally over the outer tube 46 and to weld with the adapter piece 49. If the adapter piece 49 would have a completely annular wall element, in particular the dense bonding of the part of the adapter piece 49 forming the inner gas supply channel to the hub 27 would be difficult to accomplish.

Die mit Bezug auf die Figuren 2 bis 5 beschriebene erste konkrete Ausgestaltung für den erfindungsgemäßen Brenner bietet den Vorteil, dass sich ein negativer Einfluss auf die LuftStrömung insbesondere in den radialen Luftzufuhrkanal 17 vermeiden lässt, da keine Veränderung der äußeren Nabengeometrie bzw. des Gaszufuhrrohres 41 im Vergleich zu einem Brenner mit lediglich einem Gasverteilerkanal zu erfolgen braucht. Außerdem können mit Hilfe des Adapterstücks die Strömungsquerschnitte optimal ausgenutzt werden, wodurch unnötige Druckverluste vermieden werden. Weiterhin ermöglicht die Ausgestaltung gemäß des ersten konkreten Ausführungsbeispiels eine robuste Konstruktion, die zudem ein einfaches Montieren ermöglicht.The referring to the FIGS. 2 to 5 described first specific embodiment of the burner according to the invention has the advantage that has a negative impact on the air flow In particular, in the radial air supply channel 17 can avoid, since no change in the outer hub geometry or the gas supply pipe 41 needs to be compared to a burner with only one gas distribution channel. In addition, the flow cross-sections can be optimally utilized with the aid of the adapter piece, whereby unnecessary pressure losses are avoided. Furthermore, the embodiment according to the first concrete embodiment allows a robust construction, which also allows easy mounting.

Eine zweite konkrete Ausgestaltung für den erfindungsgemäßen Brenner wird nachfolgend mit Bezug auf die Figuren 6 bis 8 beschrieben. Figur 6 zeigt die Nabe 27 des erfindungsgemäßen Brenners mit einem in ihrem Zentrum angeordneten Pilotbrenner 63 sowie dem Gaszufuhrrohr 141 in einer perspektivischen Darstellung. Zudem ist ein Brennerträger 65 zu erkennen, in dem zwei Anschlüsse 67, 69 für die beidem im Gaszufuhrrohr 141 befindlichen Gaszufuhrkanäle 135, 137 vorhanden sind.A second concrete embodiment for the burner according to the invention is described below with reference to the FIGS. 6 to 8 described. FIG. 6 shows the hub 27 of the burner according to the invention with a arranged in its center pilot burner 63 and the gas supply pipe 141 in a perspective view. In addition, a burner support 65 can be seen, in which there are two connections 67, 69 for the two gas supply ducts 135, 137 located in the gas supply pipe 141.

Das Gaszufuhrrohr 141 der zweiten konkreten Ausgestaltung ist in Figur 7 in einer perspektivischen Darstellung gezeigt. Es unterscheidet sich vom Gaszufuhrrohr 41 der ersten konkreten Ausgestaltung dadurch, dass die Gaszufuhrkanäle 135, 137 nebeneinander statt konzentrisch zueinander angeordnet sind. Die Geometrie der Gaszuführkanäle 135, 137 ist dabei so gewählt, dass zumindest am nabenseitigen Ausgangsende 71 des Gaszufuhrrohres Strömungsquerschnitte mit maximalen Strömungsflächen vorliegen.The gas supply pipe 141 of the second specific embodiment is in FIG. 7 shown in a perspective view. It differs from the gas supply pipe 41 of the first concrete embodiment in that the gas supply channels 135, 137 are arranged side by side instead of concentric with each other. The geometry of the gas supply channels 135, 137 is selected such that there are flow cross sections with maximum flow areas at least at the hub-side outlet end 71 of the gas supply tube.

Am dem nabenseitigen Ende 71 abgewandten Ende des Gaszufuhrrohrs 141 sind die beiden Gasanschlüsse für das Gaszufuhrrohr 141 angeordnet. Diese sind ebenfalls nebeneinander angeordnet, wobei jedoch eine Verbindungslinie A, die die Zentren der beiden Gasanschlüsse 67, 69 miteinander verbindet, um 90° gegenüber einer Verbindungslinie B, die die Zentren der Gaszufuhrkanäle 135, 137 am nabenseitigen Ende des Gaszufuhrrohres 141 miteinander verbindet, um 90° gedreht ist. In einem Übergangsabschnitt 73 des Gaszufuhrrohres erfolgt eine Verwindung der von den Gasanschlüssen 67, 69 ausgehenden Gaszufuhrkanäle 135, 137, durch die die Drehung der Verbindungslinien A, B realisiert wird. Gleichzeitig erfolgt in diesem Übergangsabschnitten 73 der Übergang von den kreisförmigen Strömungsquerschnitt der Anschlüsse 67, 69 zu den hinsichtlich der Strömungsflächen optimierten Strömungsquerschnitten am nabenseitigen Ende 71 des Gaszufuhrrohres 141. Eine Ansicht auf die Gasanschlüsse 67, 69 des Gaszufuhrrohres 141 ist in Figur 8 dargestellt.At the hub-side end 71 facing away from the end of the gas supply pipe 141, the two gas ports for the gas supply pipe 141 are arranged. These are also arranged side by side, but a connecting line A, which connects the centers of the two gas ports 67, 69 with each other by 90 ° with respect to a connecting line B, the centers of the gas supply channels 135, 137 at the hub end of the gas supply pipe 141 connects to each other Turned 90 °. In one Transition portion 73 of the gas supply pipe, a twisting of the gas connections 67, 69 outgoing gas supply channels 135, 137, through which the rotation of the connecting lines A, B is realized. At the same time takes place in this transition sections 73, the transition from the circular flow cross-section of the terminals 67, 69 to the flow areas optimized flow cross-sections at the hub end 71 of the gas supply pipe 141. A view of the gas ports 67, 69 of the gas supply pipe 141 is in FIG. 8 shown.

Obwohl im zweiten konkreten Ausführungsbeispiel die Gaszufuhrkanäle 35, 37 von den Gasanschlüssen 67, 69 zum nabenseitigen Ende 71 des Gaszufuhrrohres 141 hin, um 90° verwunden sind, kann die Verwindung auch um andere Winkel als 90° erfolgen, wenn eine andere Anordnung der Gasanschlüsse 67, 69 im Brennerträger 65 gewünscht ist.Although in the second concrete embodiment, the gas supply channels 35, 37 of the gas ports 67, 69 to the hub side end 71 of the gas supply pipe 141 toward, wound by 90 °, the twisting can also be done by other angles than 90 °, if another arrangement of the gas ports 67th , 69 in the burner carrier 65 is desired.

Das Gaszufuhrrohr 141 des zweiten konkreten Ausführungsbeispieles für den erfindungsgemäßen Brenner kann insbesondere als Gusskonstruktion ausgeführt sein. In einer solchen kann insbesondere bei einer Verwindung der Kanäle im Rohr um 90° eine konstante Wandstärke über das komplette Bauteil erreicht werden.The gas supply pipe 141 of the second concrete embodiment of the burner according to the invention can be designed in particular as a cast construction. In such, in particular with a twisting of the channels in the pipe by 90 °, a constant wall thickness over the entire component can be achieved.

Die Ausgestaltung des Gaszufuhrrohres 141 gemäß der zweiten konkreten Ausgestaltung bietet insbesondere den Vorteil, dass die Aufteilung der Gaszufuhrkanäle in zwei getrennte Gasanschlüsse zwischen dem Brennerträger und der Nabe erfolgt. Dies vereinfacht die Montage des Brenners. Der Brennerträgerflansch ist dann lediglich mit zwei Passbohrungen zu versehen. Zudem ändert die Rohrkonstruktion die Aerodynamik gegenüber einem Brenner mit lediglich einem Gasverteilerkanal in der Nabe kaum. Da der Übergangsabschnitt in der Nähe des Brennerträgers - und damit entfernt von den Luftkanälen des Pilotbrenners und des Hauptbrenners - angeordnet ist, führt diese Änderung des Gaszufuhrrohres gegenüber einem Gaszufuhrrohr mit lediglich einem Gaszufuhrkanal nicht zu einer wesentlichen Änderung der Aerodynamik des Brenners.The design of the gas supply pipe 141 according to the second specific embodiment offers the particular advantage that the distribution of the gas supply channels in two separate gas connections between the burner carrier and the hub takes place. This simplifies the assembly of the burner. The burner carrier flange is then only provided with two fitting holes. In addition, the tube construction hardly changes the aerodynamics compared to a burner with only one gas distribution channel in the hub. Since the transition section is located in the vicinity of the burner support - and thus away from the air ducts of the pilot burner and the main burner - this change in the gas supply pipe leads to a gas supply pipe with only one gas supply channel not to a significant change in the aerodynamics of the burner.

Claims (15)

  1. Burner having a central fuel supply arrangement (27), an annular air duct (17) surrounding the central fuel supply arrangement (27) for the supply of combustion air, and swirl blades (19) arranged in the annular air duct (17), which blades have first gas nozzles (21) for injecting a gaseous fuel into the combustion air, and second gas nozzles (23) for injecting a gaseous fuel into the combustion air, wherein the first gas nozzles (21) are supplied by a first gas distributor duct (29) in the fuel supply arrangement (27), and the second gas nozzles (23) are supplied from a second gas distributor duct (31) in the fuel supply arrangement (27), and wherein the first gas distributor duct (29) and the second gas distributor duct (31) are supplied with combustion gas by a gas supply pipe (41, 141) which is arranged offset with respect to and parallel next to a centrally arranged pilot burner and has a first gas supply duct (35, 135) and a second gas supply duct (37, 137), wherein the first gas supply duct (35, 125) is connected to the first gas distributor duct (29) and the second gas supply duct (37, 137) is connected to the second gas distributor duct (31).
  2. Burner according to Claim 1, in which the first gas supply duct (35) and the second gas supply duct (37) run coaxially with respect to one another.
  3. Burner according to Claim 2, in which the gas supply pipe (41) comprises an outer pipe (46) and an inner pipe (45), the interspace between the outer pipe (46) and the inner pipe (45) forms the first gas supply duct (35), and the interior of the inner pipe (45) forms the second gas supply duct (37).
  4. Burner according to Claim 3, characterized in that the inner pipe (45) and/or the outer pipe (46) has/have an elastic compensation element (47) which permits(s) axial expansion or compression of the inner pipe (45) with respect to the outer pipe (46).
  5. Burner according to Claim 4, in which the inner pipe (45) and/or the outer pipe (46) is/are divided into two axial parts which are connected to one another via a bellows.
  6. Burner according to one of Claims 2 to 5, in which the first gas supply duct (35) has an annular flow cross section and the second gas supply duct (37) has a circular flow cross section, and between the gas supply pipe (41) and the gas distributor ducts (29, 31) there is an adapter part (49) which converts the annular flow cross section and the circular flow cross section into cross sections with maximum flow areas for the flowing gas.
  7. Burner according to Claim 6, in which the adapter part (49) forms a part (53) of the circumference of the outer pipe (46) and the outer pipe (46) has a corresponding cutout in the circumferential wall.
  8. Burner according to one of Claims 1 to 7, in which the first gas distributor duct (29) and the second gas distributor duct (31) are supplied with combustion gas by a common gas supply pipe (141) in which the first gas supply duct (135) and the second gas supply duct (137) run next to one another.
  9. Burner according to Claim 8, in which the first gas supply duct (135) and the second gas supply duct (137) each have, at least at their ends oriented towards the gas distributor ducts (29, 31), a flow cross section with a maximum flow area for the flowing gas.
  10. Burner according to Claim 8 or Claim 9, in which
    - the first gas supply duct (135) is supplied with combustion gas via a first gas supply connection (67) and the second gas supply duct (137) is supplied with combustion gas via a second gas supply connection (69),
    - the first gas supply connection (67) and the second gas supply connection (69) are arranged adjacent to one another, and
    - there is a transition section (73) which connects the gas supply connections (67, 69) to the gas supply ducts (135, 137).
  11. Burner according to Claim 10, in which a straight line (A), connecting the first gas supply connection (67) and the second gas supply connection (69), and a straight line (B), connecting the first gas supply duct (135) and the second gas supply duct (137), enclose an angle between them.
  12. Burner according to Claim 11, in which the angle is 90 degrees.
  13. Burner according to Claim 9 and one of Claims 10 to 12, in which the gas supply connections (67, 69) each have a circular flow cross section and the transition section converts the circular flow cross sections into cross sections having maximum flow areas for the flowing gas.
  14. Burner according to one of Claims 8 to 13, in which the gas supply pipe (141) is a cast part.
  15. Gas turbine having at least one burner according to one of the preceding claims.
EP10718576.1A 2009-06-30 2010-05-05 Burner, especially for gas turbines Active EP2449310B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10718576.1A EP2449310B1 (en) 2009-06-30 2010-05-05 Burner, especially for gas turbines

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09164156A EP2270398A1 (en) 2009-06-30 2009-06-30 Burner, especially for gas turbines
EP10718576.1A EP2449310B1 (en) 2009-06-30 2010-05-05 Burner, especially for gas turbines
PCT/EP2010/056057 WO2011000615A1 (en) 2009-06-30 2010-05-05 Burner, in particular for gas turbines

Publications (2)

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EP2449310A1 EP2449310A1 (en) 2012-05-09
EP2449310B1 true EP2449310B1 (en) 2017-03-22

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EP10718576.1A Active EP2449310B1 (en) 2009-06-30 2010-05-05 Burner, especially for gas turbines

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DE102011116317A1 (en) * 2011-10-18 2013-04-18 Rolls-Royce Deutschland Ltd & Co Kg Magervormian burner of an aircraft gas turbine engine
CN107110504B (en) * 2014-11-21 2019-11-26 安萨尔多能源公司 The spray boom injector in combustion chamber for injecting fuel into combustion gas turbine
DE102022207492A1 (en) * 2022-07-21 2024-02-01 Rolls-Royce Deutschland Ltd & Co Kg Nozzle device for adding at least one gaseous fuel and one liquid fuel, set, supply system and gas turbine arrangement

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1614967A1 (en) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Method and premixed combustion system

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1204002A1 (en) * 1984-07-04 1996-08-27 А.В. Андреев Method of preparation of fuel-and-air mixture in annular combustion chamber of gas-turbine engine
EP0276696B1 (en) 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Hybrid burner for premix operation with gas and/or oil, particularly for gas turbine plants
DE59204270D1 (en) * 1991-04-25 1995-12-14 Siemens Ag BURNER ARRANGEMENT, ESPECIALLY FOR GAS TURBINES, FOR LOW POLLUTANT COMBUSTION OF COAL GAS AND OTHER FUELS.
IT1263683B (en) * 1992-08-21 1996-08-27 Westinghouse Electric Corp NOZZLE COMPLEX FOR FUEL FOR A GAS TURBINE
US5351578A (en) * 1992-11-20 1994-10-04 James Emter Resilient compressible clamping surface for circular saw blades
US5359847B1 (en) * 1993-06-01 1996-04-09 Westinghouse Electric Corp Dual fuel ultra-flow nox combustor
US5657632A (en) * 1994-11-10 1997-08-19 Westinghouse Electric Corporation Dual fuel gas turbine combustor
US5685139A (en) * 1996-03-29 1997-11-11 General Electric Company Diffusion-premix nozzle for a gas turbine combustor and related method
US6363726B1 (en) * 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
SE521293C2 (en) * 2001-02-06 2003-10-21 Volvo Aero Corp Method and apparatus for supplying fuel to a combustion chamber
EP1394471A1 (en) * 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Burner
EP1507119A1 (en) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Burner and process to operate a gas turbine
EP1568942A1 (en) * 2004-02-24 2005-08-31 Siemens Aktiengesellschaft Premix Burner and Method for Combusting a Low-calorific Gas
US6993916B2 (en) * 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1614967A1 (en) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Method and premixed combustion system

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Publication number Publication date
WO2011000615A1 (en) 2011-01-06
EP2270398A1 (en) 2011-01-05
EP2449310A1 (en) 2012-05-09
RU2533045C2 (en) 2014-11-20
CN102472494B (en) 2014-08-20
RU2012102975A (en) 2013-08-10
CN102472494A (en) 2012-05-23

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