EP1651841B1 - Open-cooled component for a gas turbine, combustion chamber, and gas turbine - Google Patents

Open-cooled component for a gas turbine, combustion chamber, and gas turbine Download PDF

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Publication number
EP1651841B1
EP1651841B1 EP04739955A EP04739955A EP1651841B1 EP 1651841 B1 EP1651841 B1 EP 1651841B1 EP 04739955 A EP04739955 A EP 04739955A EP 04739955 A EP04739955 A EP 04739955A EP 1651841 B1 EP1651841 B1 EP 1651841B1
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EP
European Patent Office
Prior art keywords
gas turbine
cavity
component
wall
combustion chamber
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EP04739955A
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German (de)
French (fr)
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EP1651841A1 (en
Inventor
Stefan Hoffmann
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Siemens AG
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Siemens AG
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Priority to EP04739955A priority Critical patent/EP1651841B1/en
Priority to PL04739955T priority patent/PL1651841T3/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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer

Definitions

  • the present invention relates to an open-cooled component for a gas turbine having a H adoptedgasbeetzmannten outer wall which at least partially defines a first cavity for a first means and are arranged in the through holes, which open through openings in the cavity and on the other hand in the hot gas space and at least one second cavity for admixing a second means in fluid communication with the passage openings.
  • the invention further relates to a combustion chamber and a gas turbine.
  • Combustor walls as well as gas turbine blades are subject to high physical stress during normal operation of the gas turbine.
  • these components are provided with a cooling. If air is used as a coolant, it is taken from a combustion chamber upstream compressor with diffuser and is lost to the combustion process. As a result, flame temperatures and NO x emissions increase.
  • the wall of a combustion chamber is cooled either open or closed.
  • the open cooling is designed as convective cooling, film cooling or as impingement cooling with a cooling air outlet in the combustion chamber.
  • the closed cooling requires a higher design effort and leads to an increased pressure loss due to the cooling air flow and the cooling itself.
  • cooling air extraction In order to reduce the negative effect caused by the cooling air extraction, it is known to add fuel. In the prior art, this is as cooling air reheating or further Meaning also known as stepped combustion.
  • a combustion chamber of a gas turbine with a plurality of hollow freestanding spokes known in the cavity of a fuel is performed.
  • the cavity is connected through openings with the combustion chamber.
  • air is supplied to the ports in a supply passage disposed in the outer wall of the spokes to receive, in conjunction with the fuel, a combustible mixture which is fed into the combustion chamber for NO x reduction during operation of the gas turbine.
  • a disadvantage of the known concepts is that for the mixing of cooling air and fuel, a volume is to be provided by the reactants by self-ignition or ignite flashback in the components. As a result, under certain circumstances, stable combustion processes develop, so that the cooling effect of the fuel-air mixture is lost or the component can be damaged by the internal combustion occurring.
  • the second cavity is formed by supply channels provided in the outer wall, which are connected via transverse channels with the through holes formed as a through-hole, so that the two means are miscible only within the through holes.
  • the invention further proposes a combustion chamber for a gas turbine with a wall element, which has a corresponding arrangement.
  • the invention turns away.
  • This allows the previously formed between the double wall second cavity be embedded as a supply channel in the outer wall, which is connected via separate transverse channels with the through holes.
  • a possibility is thus created for the first time to substantially completely avoid a mixing volume in the component, as a result of which flashback and auto-ignition in the component can be largely avoided.
  • a flame temperature increase can be reduced with open cooling, since the cooling air can now be enriched with fuel without the disadvantages described above.
  • the present invention therefore allows the cooling air flow to be increased without adversely affecting combustion.
  • the passage opening can be provided, for example, for the cooling air to flow into the combustion chamber of the combustion chamber.
  • fuel Via the supply channel provided in the outer wall of the component, fuel can be supplied which mixes with the cooling air as it flows into the passage opening and thus forms a combustible mixture.
  • a flashback is avoided insofar as there is no ignitable mixture in one of the supply channels or in the cavities before the mouth of the transverse channel in the passage opening.
  • the outer wall has a multiplicity of through-bores, a multiplicity of supply channels extending between the bores, and a multiplicity of further transverse channels crosslinking the supply channels with the through-bores. Due to the net-like structure of the channels and holes, a homogenization of the flowing mixture into the combustion chamber of fuel and cooling air can be achieved. About that In addition, it is possible to cool the component more uniformly, so that local overheating can be avoided.
  • the component has at least two interconnectable layers.
  • one layer may have the channel, while a second layer is formed on the combustion chamber side of a particularly resistant material.
  • a high load capacity of the component can be achieved.
  • the channel is introduced in at least one layer surface of one of the layers on the connection side.
  • the channel can be introduced in this way by milling or similar material-removing processes in the surface of a layer, wherein by assembling the adjacent layers closed channels are formed.
  • the channel can thereby be introduced into the component by means of known and also cost-effective methods.
  • the cavity with a first fluid source and the supply channel with a second fluid source is connectable.
  • Both fluids ie means, can be used to cool the blade so as to reduce the amount of air required for cooling. A larger amount of air is available to the combustion process, so that high flame temperatures and NO x emissions can be reduced.
  • the blade is basically the same principle as for the wall element of the combustion chamber at the bottom. Again, there is essentially no mixing volume, so that flashback and autoignition are largely avoided. The reliability of the gas turbine with respect to defective blades can be increased. As with the combustion chamber, the cooling air flow can be increased without negative effects on the combustion and the flame acoustics are detuned.
  • the invention also proposes that one of the two fluid sources is an oxidant source and the other fluid source is a fuel source.
  • an ignitable mixture is formed only in the region of the mouth of the passage opening in the flow channel of the gas turbine, when the mouth of the channels is arranged sufficiently close to the mouth of the passage opening in the flow channel.
  • the invention also proposes a gas turbine, wherein the gas turbine has a combustion chamber according to the invention.
  • the negative effects, as described above, can be largely reduced by supplying fuel, wherein the combustion chamber according to the invention enables safe operation with respect to auto-ignition and flashback. Furthermore, it is advantageous to influence the flame acoustics in order to reduce the stresses and wear caused by this.
  • the invention also proposes a gas turbine with a component designed as a blade.
  • the cooling effect for the blade of the turbine unit which can be designed as a fixed guide blade as well as a rotating blade can be improved by increasing the cooling air flow, the negative effects on the combustion can be largely avoided.
  • an influence on the detuning of the flame acoustics can be exerted. Wear and tear can be further reduced.
  • Fig. 1 shows a section through an inventive designed as a wall element 2 component with a plurality of through holes 3, can enter through the cooling air into the combustion chamber.
  • the wall element 2 also has transverse channels 4, which open at one end in each case into a passage opening 3. Via connecting channels 9, a fluid fuel can be supplied, which is guided via the transverse channels 4 to the through holes 3 and is introduced there into the flow of cooling air.
  • Fig. 2 illustrates this system of channels for the fuel supply.
  • the wall element 2 has two interconnectable layers 6, 7. In the connection-side layer surface of the layer 6, the channel system is introduced by milling. By the connection of the layers 6 and 7 closed channels 4 and 9 are formed.
  • Fig. 3 shows a plan view of the surface of the layer 6 of the wall element 2 in which the channels 4 and 9 are introduced.
  • the connecting channel 9 is formed integrally with the wall element.
  • FIG. 4 schematically shows a section of a flow channel of a gas turbine, in which a blade 10 is arranged.
  • hot gas space 21 open through holes 12, wherein in the mouth region junctions of transverse channels 13 are indicated schematically.
  • FIG. 5 A section through such a blade 10 is shown in FIG. 5.
  • a blade wall 14 encloses a cavity 15, wherein the blade wall 17 is provided with passage openings 12. Cooling air can be supplied via the cavity 15 and exits through the passage openings 12 into the flow channel 11.
  • the blade wall 14 is further provided with a system of supply channels 13, which are connected via transverse channels 4 each with the through holes 12.
  • the supply channels 13 are in fluid communication with a fluid fuel source.
  • the blade 14 is constructed in two layers, consisting of an outer layer 16 and a cavity 15 forming inner layer 17.
  • the inner layer 17 has on its side facing the layer 16 by milling introduced recesses, which the channel system with the supply channels 13 form.
  • air is conducted as cooling air for the blade 10 via through holes 12 as oxidizing agent into the flow channel 11.
  • the fluid fuel is introduced into the passage openings 12 of the blade wall 14, so that an ignitable mixture is formed.
  • the ignitable mixture is formed only in the region of the mouth of the passage openings 3, 12 in the combustion chamber or the flow channel 11 of the gas turbine. In this way, a flashback is prevented in the respective channel system with the damage caused thereby.
  • Targeted variation of the fuel supply can also influence the flame acoustics. This also has an advantageous effect on the wear and the reliability of the gas turbine.

Abstract

The invention relates to an open-cooled component for a gas turbine, said component having an outer wall (20) that is subjected to a hot gas and at least partially defines a first cavity (15) for a first means. Said outer wall is provided with through-openings (3, 12) which open up into the cavity (15) on one side and into a hot gas chamber (21) on the other. The inventive component also comprises at least one second cavity for admixing a second means, said second cavity being connected to the through-openings (3, 12) in a fluid-connected manner. The aim of the invention is to provide a component for a gas turbine, which can be used to reduce flashback and spontaneous ignition during the supply of fuel to the cooling air. To this end, the second cavity is formed by supply channels (9, 13) provided in the outer wall (20), said supply channels being connected to the through-openings (3, 12) embodied as boreholes by means of transversal channels (4) in such a way that the two means can only be mixed once inside the boreholes. The invention also relates to a combustion chamber for a gas turbine, and to a gas turbine comprising one such component.

Description

Die vorliegende Erfindung betrifft ein offen gekühltes Bauteil für eine Gasturbine mit einer heißgasbeaufschlagten Außenwand, welche zumindest teilweise einen ersten Hohlraum für ein erstes Mittel begrenzt und in der Durchgangsöffnungen angeordnet sind, welche Durchgangsöffnungen einerseits in den Hohlraum und andererseits in den Heißgasraum münden sowie mit zumindest einem zweiten Hohlraum zum Zumischen eines zweiten Mittels, der mit den Durchgangöffnungen in Strömungsverbindung steht. Die Erfindung betrifft ferner eine Brennkammer sowie eine Gasturbine.The present invention relates to an open-cooled component for a gas turbine having a Heißgasbeaufschlagten outer wall which at least partially defines a first cavity for a first means and are arranged in the through holes, which open through openings in the cavity and on the other hand in the hot gas space and at least one second cavity for admixing a second means in fluid communication with the passage openings. The invention further relates to a combustion chamber and a gas turbine.

Brennkammerwände sowie auch Gasturbinenschaufeln sind beim bestimmungsgemäßen Betrieb der Gasturbine einer hohen physikalischen Beanspruchung ausgesetzt. Um die Brennkammer sowie die Schaufel gegen die hohe Beanspruchung beständiger zu machen, sind diese Bauteile mit einer Kühlung versehen. Sofern Luft als Kühlmittel verwendet wird, wird diese aus einem der Brennkammer vorgeschalteten Verdichter mit Diffusor entnommen und geht dem Verbrennungsprozess verloren. Als Folge steigen Flammentemperaturen sowie NOx-Emissionen an.Combustor walls as well as gas turbine blades are subject to high physical stress during normal operation of the gas turbine. In order to make the combustion chamber and the blade more resistant to the high stress, these components are provided with a cooling. If air is used as a coolant, it is taken from a combustion chamber upstream compressor with diffuser and is lost to the combustion process. As a result, flame temperatures and NO x emissions increase.

Die Wand einer Brennkammer wird entweder offen oder geschlossen gekühlt. Die offene Kühlung ist dabei als konvektive Kühlung, Filmkühlung oder auch als Prallkühlung mit einem Kühlluftauslass in den Verbrennungsraum ausgebildet. Die geschlossene Kühlung erfordert einen höheren konstruktiven Aufwand und führt zu einem erhöhten Druckverlust aufgrund der Kühlluftführung und der Kühlung selbst.The wall of a combustion chamber is cooled either open or closed. The open cooling is designed as convective cooling, film cooling or as impingement cooling with a cooling air outlet in the combustion chamber. The closed cooling requires a higher design effort and leads to an increased pressure loss due to the cooling air flow and the cooling itself.

Um den negativen Effekt, den die Kühlluftentnahme verursacht, zu reduzieren, ist es bekannt Brennstoff zuzugeben. Im Stand der Technik ist dies als Kühlluftnachheizung oder im weiteren Sinne auch als gestufte Verbrennung bekannt.In order to reduce the negative effect caused by the cooling air extraction, it is known to add fuel. In the prior art, this is as cooling air reheating or further Meaning also known as stepped combustion.

Hierzu zeigt die US 5,125,793 eine Turbinenschaufel einer Gasturbine mit einer einen Hohlraum umschließenden doppelwandigen Außenwand. In der doppelwandigen Außenwand ist ein Strömungskanal für Luft angeordnet. Im Hohlraum strömt ein flüssiger Brennstoff, welcher durch Durchgangsösffnungen in den in der Doppelwand befindlichen Strömungskanal eingedüst wird und der dort auf einen Katalysator trifft. Durch den Katalysator zerlegt sich der Brennstoff endothermisch in zumindest ein brennbares Gas, was die Schaufel kühlt. Die Luft transportiert die Gase zum einem Auslass, von dem aus das Gemisch in die Turbine einströmen und dort verbrennen kann.This shows the US 5,125,793 a turbine blade of a gas turbine with a cavity enclosing a double-walled outer wall. In the double-walled outer wall, a flow channel for air is arranged. In the cavity flows a liquid fuel, which is injected through Durchgangsösffnungen in the flow channel located in the double wall and there meets a catalyst. Through the catalyst, the fuel decomposes endothermically into at least one combustible gas, which cools the blade. The air transports the gases to an outlet, from which the mixture can flow into the turbine and burn there.

Ferner ist aus der US 6,192,688 eine Brennkammer einer Gasturbine mit mehreren hohlen freistehenden Speichen bekannt, in deren Hohlraum ein Brennstoff geführt wird. Der Hohlraum ist durch Öffnungen mit dem Verbrennungsraum verbunden. In einem in der Außenwand der Speichen angeordneten Versorgungskanal wird zusätzlich Luft zu den Öffnungen geführt, um in Verbindung mit dem Brennstoff ein brennbares Gemisch zu erhalten, welches in die Brennkammer zur NOx-Reduzierung während des Betriebs der Gasturbine eingespeist wird.Furthermore, from the US 6,192,688 a combustion chamber of a gas turbine with a plurality of hollow freestanding spokes known in the cavity of a fuel is performed. The cavity is connected through openings with the combustion chamber. In addition, air is supplied to the ports in a supply passage disposed in the outer wall of the spokes to receive, in conjunction with the fuel, a combustible mixture which is fed into the combustion chamber for NO x reduction during operation of the gas turbine.

Außerdem ist aus der US 4,347,037 eine hohle Turbinenschaufel bekannt, bei der in den von Heißgas umströmbaren Seitenwände gleichmäßig verteilte Filmkühlöffnungen eingebracht sind. Für jede Filmkühlöffnung ist jeweils ein Auslasskanal vorgesehen. An deren in der Schaufelwand liegenden Eingängen münden jeweils zwei getrennte, am inneren Hohlraum der Turbinenschaufel beginnende Zuführkanäle, um die zur Filmkühlung notwendige Kühlluft vom Hohlraum zur Filmkühlöffnung führen zu können.Moreover, from the US 4,347,037 a hollow turbine blade is known in which in the hot gas flow around side walls evenly distributed film cooling holes are introduced. For each film cooling opening an outlet channel is provided in each case. At their lying in the blade wall entrances open in each case two separate, starting at the inner cavity of the turbine blade feed channels in order to be able to perform the cooling air necessary for film cooling from the cavity to the film cooling opening.

Nachteilig an den bekannten Konzepten ist, dass zur Vermischung von Kühlluft und Brennstoff ein Volumen bereitzustellen ist, indem sich die Reaktionspartner durch Selbstzündung oder Flammenrückschlag in den Bauteilen entzünden können. Hierdurch bilden sich unter Umständen stabile Verbrennungsvorgänge aus, so dass die Kühlwirkung des Brennstoff-Luftgemisches verloren geht bzw. das Bauteil durch die intern auftretende Verbrennung Schaden nehmen kann.A disadvantage of the known concepts is that for the mixing of cooling air and fuel, a volume is to be provided by the reactants by self-ignition or ignite flashback in the components. As a result, under certain circumstances, stable combustion processes develop, so that the cooling effect of the fuel-air mixture is lost or the component can be damaged by the internal combustion occurring.

Es ist daher die Aufgabe der vorliegenden Erfindung, ein Bauteil für eine Gasturbine, eine Brennkammer sowie eine Gasturbine anzugeben, mit denen die oben beschriebenen Nachteile reduziert werden können.It is therefore an object of the present invention to provide a component for a gas turbine, a combustion chamber and a gas turbine, with which the disadvantages described above can be reduced.

Die Aufgabe wird durch die Merkmale des Anspruch 1 gelöst. Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.The object is solved by the features of claim 1. Advantageous embodiments are specified in the subclaims.

Die Lösung sieht vor, dass eine getrennte Führung von Kühlmittel und Brennstoff in getrennten Kanälen erfolgt. Die Vermischung dieser beiden Mittel zu einem brennbaren Gemisch geschieht daher erst kurz vor der Ausblasung in das Heißgas. Somit wird verhindert, dass das brennbare Gemisch in den Bauteilen selber, also außerhalb des Strömungskanals und/oder außerhalb der Brennkammer, sich durch Flammenrückschlag oder Selbstentzündung entzündet.The solution provides that a separate guidance of coolant and fuel takes place in separate channels. The mixing of these two agents to a combustible mixture is therefore only shortly before blowing into the hot gas. Thus, it is prevented that the combustible mixture in the components themselves, ie outside the flow channel and / or outside of the combustion chamber, ignited by flashback or autoignition.

Dies wird erreicht, indem der zweite Hohlraum durch in der Außenwand vorgesehenen Versorgungskanäle gebildet wird, die über Querkanäle mit den als Durchgangsbohrung ausgebildeten Durchgangsöffnungen in Verbindung stehen, so dass die beiden Mittel erst innerhalb der Durchgangsbohrungen vermischbar sind.This is achieved by the second cavity is formed by supply channels provided in the outer wall, which are connected via transverse channels with the through holes formed as a through-hole, so that the two means are miscible only within the through holes.

Mit der Erfindung wird ferner eine Brennkammer für eine Gasturbine mit einem Wandelement vorgeschlagen, welches eine dementsprechende Anordnung aufweist.The invention further proposes a combustion chamber for a gas turbine with a wall element, which has a corresponding arrangement.

Von der doppelwandigen aus dem Stand der Technik bekannten Ausführung wendet sich die Erfindung ab. Dadurch kann der bisher zwischen der Doppelwand gebildete zweite Hohlraum als Versorgungskanal in die Außenwand eingebettet werden, welcher über separate Querkanäle mit den Durchgangsöffnungen verbunden wird. Hierdurch wird erstmals somit eine Möglichkeit geschaffen, ein Mischvolumen im Bauteil im wesentlichen vollständig zu vermeiden, wodurch Flammenrückschlag und Selbstzündung im Bauteil weitgehend vermieden werden können. Ferner kann mit einem als Wandelement einer Brennkammer ausgebildeten Bauteil eine Flammentemperaturerhöhung bei einer offenen Kühlung reduziert werden, da die Kühlluft nunmehr ohne die oben beschriebenen Nachteile mit Brennstoff angereichert werden kann. Die vorliegende Erfindung ermöglicht daher, dass der Kühlluftstrom ohne negative Auswirkungen auf die Verbrennung angehoben werden kann.From the double-walled known from the prior art embodiment, the invention turns away. This allows the previously formed between the double wall second cavity be embedded as a supply channel in the outer wall, which is connected via separate transverse channels with the through holes. As a result, a possibility is thus created for the first time to substantially completely avoid a mixing volume in the component, as a result of which flashback and auto-ignition in the component can be largely avoided. Furthermore, with a component designed as a wall element of a combustion chamber, a flame temperature increase can be reduced with open cooling, since the cooling air can now be enriched with fuel without the disadvantages described above. The present invention therefore allows the cooling air flow to be increased without adversely affecting combustion.

Mit der vorliegenden Erfindung kann ferner erreicht werden, dass die Flammenakustik beeinflusst, insbesondere verstimmt, werden kann. Die Durchgangsöffnung kann beispielsweise dazu vorgesehen sein, dass die Kühlluft in den Brennraum der Brennkammer strömt. Über den in der Außenwand des Bauteils vorgesehenen Versorgungskanal kann Brennstoff zugeführt werden, der sich beim Einströmen in die Durchgangsöffnung mit der Kühlluft mischt und so ein brennbares Gemisch bildet. Ein Flammenrückschlag wird insofern vermieden, als dass vor der Mündung des Querkanals in der Durchgangsöffnung kein zündfähiges Gemisch in einem der Versorgungskanäle oder in den Hohlräumen vorliegt. Somit können die oben genannten unerwünschten, teilweise gefährlichen, Zustände vermieden werden.With the present invention can also be achieved that the flame acoustics influenced, in particular detuned, can be. The passage opening can be provided, for example, for the cooling air to flow into the combustion chamber of the combustion chamber. Via the supply channel provided in the outer wall of the component, fuel can be supplied which mixes with the cooling air as it flows into the passage opening and thus forms a combustible mixture. A flashback is avoided insofar as there is no ignitable mixture in one of the supply channels or in the cavities before the mouth of the transverse channel in the passage opening. Thus, the above-mentioned undesirable, sometimes dangerous, conditions can be avoided.

In einer weiteren Ausgestaltung wird vorgeschlagen dass, die Außenwand eine Vielzahl von Durchgangsbohrungen, eine Vielzahl von zwischen den Bohrungen verlaufenden Versorgungskanälen und eine Vielzahl von die Versorgungskanäle mit den Durchgangsbohrungen vernetzenden weiteren Querkanälen aufweist. Durch die netzartige Struktur der Kanäle und Bohrungen kann eine Vergleichmäßigung des in die Brennkammer strömenden Gemisches aus Brennstoff und Kühlluft erreicht werden. Darüber hinaus besteht die Möglichkeit, das Bauteil gleichmäßiger zu kühlen, so dass lokale Überhitzungen vermieden werden können.In a further embodiment, it is proposed that the outer wall has a multiplicity of through-bores, a multiplicity of supply channels extending between the bores, and a multiplicity of further transverse channels crosslinking the supply channels with the through-bores. Due to the net-like structure of the channels and holes, a homogenization of the flowing mixture into the combustion chamber of fuel and cooling air can be achieved. About that In addition, it is possible to cool the component more uniformly, so that local overheating can be avoided.

Darüber hinaus wird vorgeschlagen, dass das Bauteil wenigstens zwei miteinander verbindbare Schichten aufweist. So kann beispielsweise eine Schicht den Kanal aufweisen, während eine zweite Schicht brennkammerseitig aus einem besonders widerstandsfähigem Werkstoff gebildet ist. Eine höhe Belastbarkeit des Bauteils kann erreicht werden.In addition, it is proposed that the component has at least two interconnectable layers. For example, one layer may have the channel, while a second layer is formed on the combustion chamber side of a particularly resistant material. A high load capacity of the component can be achieved.

Es wird ferner vorgeschlagen, dass der Kanal in wenigstens einer Schichtoberfläche einer der Schichten verbindungsseitig eingebracht ist. Der Kanal kann auf diese Weise durch Fräsen oder ähnliche Werkstoff abtragende Verfahren in die Oberfläche einer Schicht eingebracht werden, wobei durch Zusammensetzen der benachbarten Schichten geschlossene Kanäle gebildet werden. Der Kanal kann hierdurch mittels bekannter sowie auch kostengünstiger Verfahren in das Bauteil eingebracht werden.It is further proposed that the channel is introduced in at least one layer surface of one of the layers on the connection side. The channel can be introduced in this way by milling or similar material-removing processes in the surface of a layer, wherein by assembling the adjacent layers closed channels are formed. The channel can thereby be introduced into the component by means of known and also cost-effective methods.

In einer weiteren vorteilhaften Ausgestaltung wird vorgeschlagen, dass der Hohlraum mit einer ersten Fluidquelle und der Versorgungskanal mit einer zweiten Fluidquelle verbindbar ist. Beide Fluide, d.h. Mittel, können zur Kühlung der Schaufel so verwendet werden, dass die zur Kühlung erforderliche Luftmenge reduziert wird. Eine größere Luftmenge steht dem Verbrennungsprozess zur Verfügung, so dass hohe Flammentemperaturen sowie NOx-Emission reduziert werden können. Der Schaufel liegt grundsätzlich dasselbe Prinzip wie für das Wandelement der Brennkammer zu Grunde. Auch hier existiert im Wesentlichen kein Mischvolumen, so dass Flammenrückschlag und Selbstzündung weitgehend vermieden werden. Die Zuverlässigkeit der Gasturbine in Bezug auf defekte Schaufeln kann erhöht werden. Wie auch bei der Brennkammer kann der Kühlluftstrom ohne negative Auswirkungen auf die Verbrennung erhöht werden sowie die Flammenakustik verstimmt werden.In a further advantageous embodiment, it is proposed that the cavity with a first fluid source and the supply channel with a second fluid source is connectable. Both fluids, ie means, can be used to cool the blade so as to reduce the amount of air required for cooling. A larger amount of air is available to the combustion process, so that high flame temperatures and NO x emissions can be reduced. The blade is basically the same principle as for the wall element of the combustion chamber at the bottom. Again, there is essentially no mixing volume, so that flashback and autoignition are largely avoided. The reliability of the gas turbine with respect to defective blades can be increased. As with the combustion chamber, the cooling air flow can be increased without negative effects on the combustion and the flame acoustics are detuned.

Mit der Erfindung wird ferner vorgeschlagen, dass einer der beiden Fluidquellen eine Oxidationsmittelquelle und die andere Fluidquelle eine Brennstoffquelle ist. Vorteilhaft kann erreicht werden, dass ein zündfähiges Gemisch erst im Bereich der Mündung der Durchgangsöffnung in den Strömungskanal der Gasturbine entsteht, wenn die Mündung der Kanäle hinreichend nahe der Mündung der Durchgangsöffnung im Strömungskanal angeordnet ist.The invention also proposes that one of the two fluid sources is an oxidant source and the other fluid source is a fuel source. Advantageously, it can be achieved that an ignitable mixture is formed only in the region of the mouth of the passage opening in the flow channel of the gas turbine, when the mouth of the channels is arranged sufficiently close to the mouth of the passage opening in the flow channel.

Die Erfindung schlägt auch eine Gasturbine vor, wobei die Gasturbine eine erfindungsgemäße Brennkammer aufweist. Die negativen Auswirkungen, wie sie oben beschrieben sind, können durch Zuführung von Brennstoff weitgehend reduziert werden, wobei die erfindungsgemäße Brennkammer einen sicheren Betrieb hinsichtlich Selbstzündung und Flammenrückschlag ermöglicht. Ferner kann vorteilhaft auf die Flammenakustik Einfluss genommen werden, um hierdurch bedingte Beanspruchungen und Verschleiß zu reduzieren.The invention also proposes a gas turbine, wherein the gas turbine has a combustion chamber according to the invention. The negative effects, as described above, can be largely reduced by supplying fuel, wherein the combustion chamber according to the invention enables safe operation with respect to auto-ignition and flashback. Furthermore, it is advantageous to influence the flame acoustics in order to reduce the stresses and wear caused by this.

Die Erfindung schlägt darüber hinaus eine Gasturbine mit einem als Schaufel ausgebildeten Bauteil vor. Die Kühlwirkung für die Schaufel der Turbineneinheit, welche als feststehende Leitschaufel sowie auch als rotierende Laufschaufel ausgebildet sein kann, kann durch Erhöhung der Kühlluftströmung verbessert werden, wobei die negativen Auswirkungen auf die Verbrennung weitgehend vermieden werden können. Auch mit dieser erfindungsgemäßen Ausgestaltung lässt sich ein Einfluss auf das Verstimmen der Flammenakustik ausüben. Verschleißerscheinungen können weiter reduziert werden.The invention also proposes a gas turbine with a component designed as a blade. The cooling effect for the blade of the turbine unit, which can be designed as a fixed guide blade as well as a rotating blade can be improved by increasing the cooling air flow, the negative effects on the combustion can be largely avoided. With this embodiment according to the invention, too, an influence on the detuning of the flame acoustics can be exerted. Wear and tear can be further reduced.

Weitere Vorteile und Merkmale sind der folgenden Beschreibung von Ausführungsbeispielen zu entnehmen. Im Wesentlichen gleichbleibende Elemente sind mit den gleichen Bezugszeichen bezeichnet. Ferner wird bezüglich gleicher Merkmale und Funktionen auf die Beschreibung zum Ausführungsbeispiel in Fig. 1 verwiesen.Further advantages and features can be found in the following description of exemplary embodiments. Substantially identical elements are designated by the same reference numerals. Furthermore, reference is made to the description of the exemplary embodiment in FIG. 1 with regard to the same features and functions.

Es zeigen:

Fig. 1:
einen Schnitt durch ein erfindungsgemäßes Wandelement für eine Brennkammer,
Fig. 2:
einen Schnitt durch das Wandelement in Fig. 1 entlang einer Linie I-I,
Fig. 3:
eine schematische Darstellung eines Systems von Kanälen in einem Wandelement gemäß der vorliegenden Erfindung,
Fig. 4:
eine schematische Darstellung einer Schaufel in einem Strömungskanal einer Gasturbine und
Fig. 5:
einen Schnitt durch eine erfindungsgemäße Schaufel.
Show it:
Fig. 1:
a section through a wall element according to the invention for a combustion chamber,
Fig. 2:
a section through the wall element in Fig. 1 along a line II,
3:
a schematic representation of a system of channels in a wall element according to the present invention,
4:
a schematic representation of a blade in a flow channel of a gas turbine and
Fig. 5:
a section through a blade according to the invention.

Fig. 1 zeigt einen Schnitt durch ein erfindungsgemäßes als Wandelement 2 ausgebildetes Bauteil mit einer Vielzahl von Durchgangsöffnungen 3, durch die Kühlluft in die Brennkammer eintreten kann. Das Wandelement 2 weist ferner Querkanäle 4 auf, die mit einem Ende jeweils in eine Durchgangsöffnung 3 münden. Über Verbindungskanäle 9 ist ein fluider Brennstoff zuführbar, der über die Querkanäle 4 zu den Durchgangsöffnungen 3 geführt wird und dort in die Strömung der Kühlluft eingeleitet wird. Fig. 2 verdeutlicht dieses System von Kanälen für die Brennstoffzufuhr. Das Wandelement 2 weist zwei miteinander verbindbare Schichten 6, 7 auf. In der verbindungsseitigen Schichtoberfläche der Schicht 6 ist das Kanalsystem durch Fräsen eingebracht. Durch die Verbindung der Schichten 6 und 7 werden geschlossene Kanäle 4 und 9 gebildet.Fig. 1 shows a section through an inventive designed as a wall element 2 component with a plurality of through holes 3, can enter through the cooling air into the combustion chamber. The wall element 2 also has transverse channels 4, which open at one end in each case into a passage opening 3. Via connecting channels 9, a fluid fuel can be supplied, which is guided via the transverse channels 4 to the through holes 3 and is introduced there into the flow of cooling air. Fig. 2 illustrates this system of channels for the fuel supply. The wall element 2 has two interconnectable layers 6, 7. In the connection-side layer surface of the layer 6, the channel system is introduced by milling. By the connection of the layers 6 and 7 closed channels 4 and 9 are formed.

Fig. 3 zeigt eine Draufsicht auf die Oberfläche der Schicht 6 des Wandelements 2 in dem die Kanäle 4 und 9 eingebracht sind. Der Verbindungskanal 9 ist einstückig mit dem Wandelement ausgebildet.Fig. 3 shows a plan view of the surface of the layer 6 of the wall element 2 in which the channels 4 and 9 are introduced. The connecting channel 9 is formed integrally with the wall element.

In der vorliegenden Ausgestaltung ist die Brennkammer aus einer Vielzahl von Wandelementen 2 modular aufgebaut. Das Wandelement 2 kann vorteilhaft auch als Hitzeschild, Liner und dergleichen verwendet werden.In the present embodiment, the combustion chamber of a plurality of wall elements 2 is modular. The wall element 2 can also be advantageously used as a heat shield, liner and the like.

In Fig. 4 ist ein Ausschnitt aus einem Strömungskanal einer Gasturbine schematisch dargestellt, in dem eine Schaufel 10 angeordnet ist. In den als Strömungskanal 11 ausgebildeten Heißgasraum 21 münden Durchgangsöffnungen 12, wobei in deren Mündungsbereich Einmündungen von Querkanälen 13 schematisch angedeutet sind.FIG. 4 schematically shows a section of a flow channel of a gas turbine, in which a blade 10 is arranged. In the formed as a flow channel 11 hot gas space 21 open through holes 12, wherein in the mouth region junctions of transverse channels 13 are indicated schematically.

Einen Schnitt durch eine solche Schaufel 10 zeigt Fig. 5. In dieser Ausgestaltung umschließt eine Schaufelwand 14 einen Hohlraum 15, wobei die Schaufelwand 17 mit Durchgangsöffnungen 12 versehen ist. Über den Hohlraum 15 ist Kühlluft zuführbar, die durch die Durchgangsöffnungen 12 in den Strömungskanal 11 austritt. Die Schaufelwand 14 ist ferner mit einem System aus Versorgungskanälen 13 versehen, die über Querkanäle 4 jeweils mit den Durchgangsöffnungen 12 verbunden sind. Die Versorgungskanäle 13 sind mit einer fluiden Brennstoffquelle in strömungstechnischer Verbindung. In dieser Ausgestaltung ist die Schaufel 14 zweischichtig aufgebaut, bestehend aus einer äußeren Schicht 16 sowie einer den Hohlraum 15 bildenden inneren Schicht 17. Die innere Schicht 17 weist auf ihrer der Schicht 16 zugewandten Seite durch Fräsen eingebrachte Ausnehmungen auf, die das Kanalsystem mit den Versorgungskanälen 13 bilden.A section through such a blade 10 is shown in FIG. 5. In this embodiment, a blade wall 14 encloses a cavity 15, wherein the blade wall 17 is provided with passage openings 12. Cooling air can be supplied via the cavity 15 and exits through the passage openings 12 into the flow channel 11. The blade wall 14 is further provided with a system of supply channels 13, which are connected via transverse channels 4 each with the through holes 12. The supply channels 13 are in fluid communication with a fluid fuel source. In this embodiment, the blade 14 is constructed in two layers, consisting of an outer layer 16 and a cavity 15 forming inner layer 17. The inner layer 17 has on its side facing the layer 16 by milling introduced recesses, which the channel system with the supply channels 13 form.

Erfindungsgemäß wird Luft als Kühlluft für die Schaufel 10 über Durchgangsöffnungen 12 als Oxidationsmittel in den Strömungskanal 11 geführt. An der Einmündung des Querkanals 13 wird der fluide Brennstoff in die Durchgangsöffnungen 12 der Schaufelwand 14 eingeleitet, so dass ein zündfähiges Gemisch entsteht.According to the invention, air is conducted as cooling air for the blade 10 via through holes 12 as oxidizing agent into the flow channel 11. At the junction of the transverse channel 13, the fluid fuel is introduced into the passage openings 12 of the blade wall 14, so that an ignitable mixture is formed.

Hinsichtlich des Wandelements 2 der Brennkammer wird Luft als Kühlmittel und Oxidationsmittel durch die Durchgangsöffnung 3 des Wandelements 2 in die Brennkammer geführt. Zugleich wird in die Kühlluftströmung im Bereich der Kanalmündung 5 des Querkanals 4 ein fluider Brennstoff in die Kühlluft eingeführt, so dass ebenfalls ein zündfähiges Gemisch entsteht.With regard to the wall element 2 of the combustion chamber, air is conducted as coolant and oxidant through the passage opening 3 of the wall element 2 into the combustion chamber. At the same time a fluid fuel is introduced into the cooling air in the cooling air flow in the region of the channel mouth 5 of the transverse channel 4, so that also an ignitable mixture is formed.

Aus dem Vorliegenden ergibt sich, dass das zündfähige Gemisch erst im Bereich der Mündung der Durchgangsöffnungen 3, 12 in die Brennkammer bzw. den Strömungskanal 11 der Gasturbine entsteht. Auf diese Weise wird ein Flammenrückschlag in das jeweilige Kanalsystem hinein mit den hierdurch verursachten Schäden verhindert. Durch gezielte Variation der Brennstoffzufuhr kann darüber hinaus die Flammenakustik beeinflusst werden. Dies wirkt sich ebenfalls vorteilhaft auf den Verschleiss und die Zuverlässigkeit der Gasturbine aus.From the foregoing it follows that the ignitable mixture is formed only in the region of the mouth of the passage openings 3, 12 in the combustion chamber or the flow channel 11 of the gas turbine. In this way, a flashback is prevented in the respective channel system with the damage caused thereby. Targeted variation of the fuel supply can also influence the flame acoustics. This also has an advantageous effect on the wear and the reliability of the gas turbine.

Die in den Figuren dargestellten Ausführungsbeispiele dienen lediglich der Erläuterung der Erfindung und sind für diese nicht beschränkend. So können insbesondere die Zahl und Anordnung der Kanäle und Durchgangsöffnungen sowie auch die Verfahren zur Herstellung variiert werden, ohne den Schutzbereich der Erfindung zu verlassen. Auch eine Verwendung anderer Fluide als Luft wie beispielsweise Stickstoff, Kohlendioxid oder auch flüssige Stoffe kann im Rahmen der Erfindung vorgesehen sein. Insbesondere ist auch eine Kombination eines bereits vorhanden Kühlsystems mit der vorliegenden Erfindung umfasst.The exemplary embodiments illustrated in the figures merely serve to explain the invention and are not restrictive of it. Thus, in particular, the number and arrangement of the channels and through-openings as well as the methods of production can be varied without departing from the scope of the invention. A use of fluids other than air such as nitrogen, carbon dioxide or liquid substances may be provided within the scope of the invention. In particular, a combination of an already existing cooling system with the present invention is also included.

Claims (10)

  1. Open-cooled component for a gas turbine having an outer wall (20) which is subjected to hot gas and which at least partly defines a first cavity (15) for a first medium and in which through-openings (3, 12) are arranged, which through-openings (3, 12) open into the cavity (15) on the one side and into the hot-gas space (21) on the other side, and having at least one second cavity for admixing a second medium, this second cavity being fluidically connected to the through-openings (3, 12), characterized in that the second cavity is formed by supply passages (9, 13) which are provided in the outer wall (20) and are connected via transverse passages (4) to the through-openings (3, 12) designed as through-bores, so that the two media cannot be mixed until inside the through-bores.
  2. Component according to Claim 1, characterized in that the outer wall (20) has a multiplicity of through-bores, a multiplicity of supply passages (9, 13) running between the bores and a multiplicity of further transverse passages (4) linking the supply passages (9, 13) with the through-bores.
  3. Component according to Claim 1 or 2, characterized in that the outer wall (20) has at least two layers (6, 7, 16, 17) which can be connected to one another.
  4. Component according to Claim 1, 2 or 3, characterized in that the passages (4, 9, 13) are incorporated between the two layers (6, 7) in at least one layer surface (6).
  5. Component according to one of Claims 1 to 4, characterized in that the first cavity (15) can be connected to a first fluid source and the supply passages (9, 13) can be connected to a second fluid source.
  6. Component according to Claim 5, characterized in that one of the two fluid sources is an oxidation source and the other fluid source is a fuel source.
  7. Component according to one of Claims 1 to 4, characterized in that the component is a wall element (2) of a combustion chamber or a blade (10) of a gas turbine.
  8. Combustion chamber for a gas turbine, having a component designed as a wall element (2) according to one of Claims 1 to 7.
  9. Gas turbine for a combustion chamber according to Claim 8.
  10. Gas turbine having a component designed as a blade according to one of Claims 1 to 7.
EP04739955A 2003-07-04 2004-06-16 Open-cooled component for a gas turbine, combustion chamber, and gas turbine Not-in-force EP1651841B1 (en)

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PL04739955T PL1651841T3 (en) 2003-07-04 2004-06-16 Open-cooled component for a gas turbine, combustion chamber, and gas turbine

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US8347632B2 (en) 2013-01-08
ES2288687T3 (en) 2008-01-16
CN1806094A (en) 2006-07-19
US7658076B2 (en) 2010-02-09
CN100353032C (en) 2007-12-05
EP1651841A1 (en) 2006-05-03
PL1651841T3 (en) 2008-01-31
DE502004004752D1 (en) 2007-10-04
US20100083665A1 (en) 2010-04-08
US20070101722A1 (en) 2007-05-10
WO2005003517A1 (en) 2005-01-13

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