EP2853689A1 - Arrangement of cooling channels in a turbine blade - Google Patents

Arrangement of cooling channels in a turbine blade Download PDF

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Publication number
EP2853689A1
EP2853689A1 EP13185944.9A EP13185944A EP2853689A1 EP 2853689 A1 EP2853689 A1 EP 2853689A1 EP 13185944 A EP13185944 A EP 13185944A EP 2853689 A1 EP2853689 A1 EP 2853689A1
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EP
European Patent Office
Prior art keywords
cooling
blade
arrangement
cooling channels
turbine blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP13185944.9A
Other languages
German (de)
French (fr)
Inventor
Fathi Ahmad
Thomas Burzych
Eugen Hummel
Gordon Emanuel Kunze
Frank PREUTEN
Thomas Alexis Schneider
Hannes Teuber
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP13185944.9A priority Critical patent/EP2853689A1/en
Priority to CN201480052859.5A priority patent/CN105593471A/en
Priority to JP2016516886A priority patent/JP2016533446A/en
Priority to PCT/EP2014/069747 priority patent/WO2015044007A1/en
Priority to EP14772098.1A priority patent/EP3022397A1/en
Priority to US15/023,392 priority patent/US20160208622A1/en
Publication of EP2853689A1 publication Critical patent/EP2853689A1/en
Withdrawn legal-status Critical Current

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    • 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
    • F01D5/187—Convection 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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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

Definitions

  • the invention relates to an arrangement of cooling channels in a turbine blade.
  • Turbine blades in particular blades of gas turbines, are highly stressed components. The rotation takes place during operation with a high number of revolutions. Therefore, a high mechanical load capacity is required. In addition, high temperatures occur especially in gas turbine blades during operation. It generally applies that higher temperatures of the turbine blades driving gas mixture have a favorable effect on the efficiency of the gas turbine. In order to prevent too high temperatures of the turbine blades, the turbine blades are cooled. For this purpose, cooling channels are often arranged inside the turbine blades.
  • the object of the invention is to mitigate this disadvantage.
  • An arrangement of a plurality of cooling channels, that is to say at least two cooling channels, within a turbine blade for conveying cooling fluid is proposed.
  • the cooling fluid is usually air.
  • the cooling channels lead through the turbine blade to one or more cooling fluid outlets.
  • the turbine blade regularly has a blade root, an airfoil tip, an inlet edge and a trailing edge.
  • the cooling channels are connected to each other at selected locations and are separated from each other in other areas, that when the turbine blade is damaged in the region of a cooling channel, the cooling by the other cooling channels remains largely unimpaired.
  • a cooling passage generally runs from the blade root to the blade tip along the leading edge.
  • a leak caused by damage in this cooling channel causes the cooling fluid to escape there. This is problematic because cooling occurs downstream of the leak.
  • cooling fluid can pass from one cooling channel into another cooling channel. Should a leak have occurred in the other cooling channel upstream of the connection, cooling would be lost without the connection downstream. Through the connection, the cooling can be largely maintained downstream of the connection. But it is also necessary to separate the cooling channels in other areas from each other. Without the separation cooling fluid could pass unhindered in the event of a leak to the leak, so that the cooling would in turn be more affected. Above all, it is also normal, So in the absence of leakage, a channel structure, that is, a separation of the cooling channels, required to actually direct the cooling fluid through the entire turbine blade.
  • cooling fluid would flow from a cooling fluid inlet a short distance to a cooling fluid outlet. It is therefore always a reasonable compromise between connections of the cooling channels and separate areas to create.
  • those skilled in the art can provide a variety of different arrangements.
  • the cooling channels are connected to one another in such a way that, as the arrangement flows through, cooling fluid regularly flows from one cooling channel into another cooling channel. It would also be conceivable to provide this only in the event of a leak. For the purpose of an efficient flow, it has been found useful to provide this in normal operation.
  • the cooling channels are separated from an inner wall of the turbine blade by a perforated plate or a device in the manner of a perforated plate, so that the cooling fluid can pass largely perpendicular to the inner wall of the turbine blade.
  • This achieves so-called impingement cooling.
  • This is efficient because the cooling fluid is swirled on the inner wall and flows out again after the heating. If the cooling fluid only flow past the inner wall of the turbine blade, a film lying directly against the wall could form, in which the flow is comparatively weak. In addition, in one area just heated cooling fluid would be used to cool other areas.
  • At least one cooling passage begins at the blade root in a region near the leading edge of the turbine blade.
  • the inlet for the cooling fluid is, even with the arrangements known in the prior art, for structural reasons regularly at the blade root. Since at the leading edge, the turbine blade driving gas mixture is hottest, the thermal load of the turbine blade is highest there. Therefore, it makes sense that a cooling duct begins in the area of the leading edge.
  • At least one cooling channel begins in a region near the leading edge and near the blade root and leads as a diagonal channel through the turbine blade into a region near the trailing edge and near the blade tip. It should be made clear that the diagonal canal does not have to start at the blade root and not at the entrance but only in this area. A beginning at the blade root and at the leading edge but should not be excluded. The same applies to the end of the diagonal channel near the trailing edge and near the blade tip. The diagonal canal Allows the cooling fluid to flow well into different areas of the turbine blade and provide efficient cooling anywhere.
  • two cooling channels begin at the blade root in a region near the leading edge, which end in a region near the blade root and are connected to one another and to the diagonal channel.
  • This cooling fluid can pass fromméfluideinlässen the blade root to Diagonalkanal. If cooling fluid escapes from one of the aforementioned cooling channels due to a leak, the diagonal channel can continue to be supplied with cooling fluid through the other cooling channel.
  • cooling channels branch off from the diagonal channel, wherein, in particular, cooling channels branch off in the direction of the outlet edge and / or branches off cooling channels in the direction of the blade blade tip. In this way, the distribution of the cooling fluid in the entire region of the turbine blade can be further optimized.
  • a cooling channel runs parallel to the blade tip, into which opening the above-mentioned cooling channels extending in the direction of the blade tip.
  • the cooling channel running parallel to the blade tip can open into the same region as the diagonal channel.
  • the cooling channels branching off in the direction of the outlet edge run largely perpendicular to the outlet edge.
  • the cooling channels extending in the direction of the blade tip extend largely parallel to the outlet edge. This also serves to further optimize the distribution of the cooling fluid. It is always important to keep in mind that a leak at one point should affect the cooling of the turbine blade as little as possible.
  • cooling fluid outlets are provided in the region of the outlet edge through which cooling fluid can pass from the region inside the turbine blade into an area outside the turbine blade. This can be achieved in the region of the trailing edge on an outer wall, a further cooling.
  • the leaked cooling fluid can optionally be used to drive a further turbine stage.
  • At least one cooling fluid outlet is provided on the blade root in the region of the outlet edge.
  • the cooling fluid can flow from the cooling fluid inlet, which is normally located on the blade root in the region of the leading edge, through the turbine blade and flow back to the blade root in the area of the outlet edge.
  • the exiting cooling fluid can be reused to cool additional turbine blades.
  • a blade root 2 with which the turbine blade is attached to a rotor.
  • On the left is an entrance edge 3 can be seen.
  • the leading edge 3 is the area to which a gas mixture driving the turbine blade first impinges.
  • Above a blade tip 4 can be seen.
  • a trailing edge 5 is arranged.
  • the turbine blade is not flat, but curved. In this case, the leading edge 3 and the trailing edge 5 may be straight, but also curved.
  • the blade root 2 and the blade tip run as well as the rest of the blade area curved in any case. The curvature is due to an aerodynamic shape of the turbine blade.
  • the turbine blade has a front wall (not shown) extending from the leading edge to the trailing edge and a rear wall extending at a distance therefrom which again leads from the trailing edge to the leading edge.
  • a front wall (not shown) extending from the leading edge to the trailing edge and a rear wall extending at a distance therefrom which again leads from the trailing edge to the leading edge.
  • the distance between the front wall and the rear wall in the region of the leading edge 3 and the trailing edge 5 is very low and increases toward the blade center.
  • a first cooling channel 6 begins at the blade root 2 and runs directly along the leading edge 3.
  • a further cooling channel 7 extends away from the blade root 2 and is separated from the cooling channel 6.
  • the cooling channels 6 and 7 open into a region 8, which is near the leading edge 3 and near the blade root 2.
  • the cooling channels 6 and 7 are interconnected.
  • a diagonal channel 9 which leads into a region 10 near the trailing edge 5 and near the blade tip 4, also begins.
  • a cooling channel 11 extends parallel to the blade root 2.
  • the cooling channel 11 opens into a parallel to the trailing edge 5 extending cooling channel 12. If you follow the diagonal channel 9 from the area 8 near the leading edge 3 to the area 10 near the trailing edge 5 branches two cooling channels 13 and 14, which run parallel to the cooling channel 11 and open into the cooling channel 12.
  • cooling channels 15 and 16 extending parallel to the leading edge 3 branch off from the diagonal channel 8. These lead into a cooling channel 17, which runs parallel to the blade tip 4 in the vicinity of the blade tip 4 and opens into the region 10 and is connected there to the diagonal channel 9.
  • the region 10 is also connected to the cooling channel 12 running along the trailing edge 5.
  • the cooling channel 12 opens in the blade root 2 in a cooling fluid outlet 18.
  • cooling fluid outlets 19a to 19g are provided at the trailing edge 5.
  • the arrangement 1 of the cooling channels 6, 7, 9, 11, 12, 13, 14, 15, 16, 17 can also be referred to as "fir tree design".

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Die Erfindung betrifft eine Anordnung (1) von mehreren Kühlkanälen (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) innerhalb einer Turbinenschaufel zur Förderung von Kühlfluid, wobei die Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) durch die Turbinenschaufel, welche einen Schaufelfuß (2), eine Schaufelblattspitze (4), eine Eintrittskante (3) und eine Austrittskante (5) aufweist, zu einem oder mehreren Kühlfluidauslässen (18, 19a-19g) führen, wobei die Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) so an ausgewählten Stellen (8, 10) miteinander verbunden sind und in anderen Bereichen voneinander getrennt verlaufen, dass bei einer Beschädigung der Turbinenschaufel im Bereich eines Kühlkanals (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) die Kühlung durch die anderen Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) weitgehend unbeeinträchtigt bleibt.The invention relates to an arrangement (1) of a plurality of cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) within a turbine blade for conveying cooling fluid, wherein the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) through the turbine blade having a blade root (2), an airfoil tip (4), an entry edge (3) and an exit edge (5) to one or more cooling fluid outlets (11 18, 19a-19g), wherein the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) are connected to each other at selected locations (8, 10) and separated from each other in other areas run in the event of damage to the turbine blade in the region of a cooling channel (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) cooling by the other cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) remains largely unimpaired.

Description

Die Erfindung betrifft eine Anordnung von Kühlkanälen in einer Turbinenschaufel.The invention relates to an arrangement of cooling channels in a turbine blade.

Turbinenschaufeln, insbesondere Schaufeln von Gasturbinen, sind hochbelastete Bauteile. Die Rotation erfolgt im Betrieb mit einer hohen Umdrehungszahl. Daher ist eine hohe mechanische Belastbarkeit erforderlich. Darüber hinaus treten vor allem bei Gasturbinenschaufeln im Betrieb hohe Temperaturen auf. Dabei gilt generell, dass höhere Temperaturen des die Turbinenschaufeln antreibenden Gasgemischs sich günstig auf den Wirkungsgrad der Gasturbine auswirken. Um dabei zu hohe Temperaturen der Turbinenschaufeln zu verhindern, werden die Turbinenschaufeln gekühlt. Dazu sind im Inneren der Turbinenschaufeln oft Kühlkanäle angeordnet.Turbine blades, in particular blades of gas turbines, are highly stressed components. The rotation takes place during operation with a high number of revolutions. Therefore, a high mechanical load capacity is required. In addition, high temperatures occur especially in gas turbine blades during operation. It generally applies that higher temperatures of the turbine blades driving gas mixture have a favorable effect on the efficiency of the gas turbine. In order to prevent too high temperatures of the turbine blades, the turbine blades are cooled. For this purpose, cooling channels are often arranged inside the turbine blades.

Bisweilen werden die Turbinenschaufeln durch auftreffende Fremdkörper beschädigt. Dies kann dazu führen, dass Luft aus den Kühlkanälen austritt und die Kühlung der Turbinenschaufel mitunter erheblich beeinträchtigt. Dies führt häufig dazu, dass die beschädigte Schaufel rasch ausgewechselt werden muss. Aufgabe der Erfindung ist es diesen Nachteil abzumildern.Sometimes the turbine blades are damaged by impinging foreign bodies. This can cause air to escape from the cooling channels and sometimes significantly affect cooling of the turbine blade. This often causes the damaged blade to be replaced quickly. The object of the invention is to mitigate this disadvantage.

Diese Aufgabe wird durch den unabhängigen Anspruch gelöst. Vorteilhafte Ausgestaltungen finden sich in den Unteransprüchen.This object is solved by the independent claim. Advantageous embodiments can be found in the subclaims.

Es wird eine Anordnung von mehreren Kühlkanälen, das heißt mindestens zwei Kühlkanälen, innerhalb einer Turbinenschaufel zur Förderung von Kühlfluid vorgeschlagen. Beim Kühlfluid handelt es sich im Regelfall um Luft.
Die Kühlkanäle führen durch die Turbinenschaufel zu einem oder mehreren Kühlfluidauslässen.An arrangement of a plurality of cooling channels, that is to say at least two cooling channels, within a turbine blade for conveying cooling fluid is proposed. The cooling fluid is usually air.
The cooling channels lead through the turbine blade to one or more cooling fluid outlets.

Die Turbinenschaufel weist dabei regelmäßig einen Schaufelfuß, eine Schaufelblattspitze, eine Eintrittskante und eine Austrittskante auf.The turbine blade regularly has a blade root, an airfoil tip, an inlet edge and a trailing edge.

Die Kühlkanäle sind dabei an ausgewählten Stellen so miteinander verbunden und verlaufen in anderen Bereichen so voneinander getrennt, dass bei einer Beschädigung der Turbinenschaufel im Bereich eines Kühlkanals die Kühlung durch die anderen Kühlkanäle weitgehend unbeeinträchtigt bleibt.The cooling channels are connected to each other at selected locations and are separated from each other in other areas, that when the turbine blade is damaged in the region of a cooling channel, the cooling by the other cooling channels remains largely unimpaired.

Im Stand der Technik verläuft in der Regel ein Kühlkanal vom Schaufelfuß zur Schaufelblattspitze längs der Eintrittskante. Ein Leck durch eine Beschädigung in diesem Kühlkanal hat zur Folge, dass das Kühlfluid dort austritt. Dies ist problematisch, da im stromabwärts des Lecks liegenden Bereichs die Kühlung ausfällt.In the prior art, a cooling passage generally runs from the blade root to the blade tip along the leading edge. A leak caused by damage in this cooling channel causes the cooling fluid to escape there. This is problematic because cooling occurs downstream of the leak.

Besonders problematisch wird es allerdings, wenn das Kühlfluid aus diesem Kühlkanal weiter durch die Turbinenschaufel mäandrieren soll und für Kühlung sorgen soll. Im Falle eines Lecks fällt die Kühlung der Turbinenschaufel dann weitgehend aus.It is particularly problematic, however, if the cooling fluid from this cooling channel further meander through the turbine blade and should provide cooling. In the event of a leak, the cooling of the turbine blade then largely fails.

Durch das oben vorgestellte Konzept, wonach die Kühlkanäle an ausgewählten Stellen miteinander verbunden sind und in anderen Bereichen voneinander getrennt sind, kann dieses Problem reduziert werden. Durch die Verbindungen an ausgewählten Stellen, kann Kühlfluid von einem Kühlkanal in einen anderen Kühlkanal gelangen. Sollte im anderen Kühlkanal stromaufwärts der Verbindung ein Leck aufgetreten sein, würde ohne die Verbindung stromabwärts die Kühlung ausfallen. Durch die Verbindung kann stromabwärts der Verbindung die Kühlung weitgehend aufrechterhalten werden. Es ist aber auch notwendig die Kühlkanäle in anderen Bereichen voneinander zu trennen. Ohne die Trennung könnte Kühlfluid im Falle eines Lecks ungehindert zum Leck gelangen, so dass die Kühlung wiederum stärker beeinträchtigt würde. Vor allem aber ist auch im Normalfall, also bei fehlendem Leck, eine Kanalstruktur, das heißt auch eine Trennung der Kühlkanäle, erforderlich, um das Kühlfluid tatsächlich durch die ganze Turbinenschaufel zu leiten. Anderenfalls würde das Kühlfluid von einem Kühlfluideinlass auf kurzem Wege zu einem Kühlfluidauslass strömen. Es ist also stets ein vernünftiger Kompromiss zwischen Verbindungen der Kühlkanäle und abgetrennten Bereichen zu schaffen. Unter Berücksichtigung der obigen Ausführungen kann der Fachmann eine Vielzahl von verschiedenen Anordnungen schaffen.By the concept presented above, according to which the cooling channels are connected at selected locations and are separated from each other in other areas, this problem can be reduced. Due to the connections at selected points, cooling fluid can pass from one cooling channel into another cooling channel. Should a leak have occurred in the other cooling channel upstream of the connection, cooling would be lost without the connection downstream. Through the connection, the cooling can be largely maintained downstream of the connection. But it is also necessary to separate the cooling channels in other areas from each other. Without the separation cooling fluid could pass unhindered in the event of a leak to the leak, so that the cooling would in turn be more affected. Above all, it is also normal, So in the absence of leakage, a channel structure, that is, a separation of the cooling channels, required to actually direct the cooling fluid through the entire turbine blade. Otherwise, the cooling fluid would flow from a cooling fluid inlet a short distance to a cooling fluid outlet. It is therefore always a reasonable compromise between connections of the cooling channels and separate areas to create. In view of the above, those skilled in the art can provide a variety of different arrangements.

Auch mit der oben beschriebenen Anordnung ist im Falle eines Lecks nicht zu vermeiden, dass die Kühlung beeinträchtigt wird und in einzelnen Bereichen auch ausfällt. Insgesamt aber wird der Kühlfluidverlust deutlich reduziert und im intakten Schaufelbereich ist die Kühlung überwiegend gewährleistet. Damit bleiben die mechanische Stabilität und die Festigkeit weitgehend unbeeinträchtigt. Damit kann die beschädigte Turbinenschaufel weiter betrieben werden.Even with the arrangement described above, in the case of a leak can not be avoided that the cooling is impaired and in some areas also fails. Overall, however, the cooling fluid loss is significantly reduced and in the intact blade area, the cooling is predominantly ensured. Thus, the mechanical stability and strength remain largely unaffected. This allows the damaged turbine blade to continue to operate.

Auch wenn es langfristig notwendig bleiben sollte, die Turbinenschaufel auszutauschen, ist es ein großer Vorteil, wenn dies erst bei der nächsten regulären größeren Wartung der Turbine erfolgen muss. Die erhöhte Temperatur führt oft nicht sofort zu einer nicht mehr hinnehmbaren Beschädigung der Turbinenschaufel sondern erst nach längerem Betrieb bei Überhitzung.Although it should remain necessary in the long term to replace the turbine blade, it is a great advantage if this has to be done at the next regular major maintenance of the turbine. The increased temperature often does not immediately lead to unacceptable damage to the turbine blade, but only after prolonged operation in the event of overheating.

Wenngleich die Darstellung vor allem in Hinblick auf die Kühlung von Laufschaufeln, die mit dem Schaufelfuß an einem Rotor befestigt sind, gewählt worden ist, ist das vorgestellte Kühlkonzept auch für Leitschaufeln grundsätzlich anwendbar.Although the illustration has been selected above all with regard to the cooling of rotor blades which are fastened to a rotor with the blade root, the cooling concept presented is also applicable in principle to guide blades.

In einer Ausführungsform der Erfindung ist vorgesehen, dass die Kühlkanäle so miteinander verbunden sind, dass bei Durchströmung der Anordnung regelmäßig Kühlfluid von einem Kühlkanal in einen anderen Kühlkanal strömt. Es wäre zwar auch denkbar, dies nur im Falle eines Lecks vorzusehen. Im Sinne einer effizienten Durchströmung hat es sich als sinnvoll herausgestellt dies auch im Normalbetrieb vorzusehen.In one embodiment of the invention, it is provided that the cooling channels are connected to one another in such a way that, as the arrangement flows through, cooling fluid regularly flows from one cooling channel into another cooling channel. It would also be conceivable to provide this only in the event of a leak. For the purpose of an efficient flow, it has been found useful to provide this in normal operation.

In einer Ausführungsform der Erfindung sind die Kühlkanäle von einer Innenwand der Turbinenschaufel durch ein Lochblech oder eine Vorrichtung nach Art eines Lochblechs getrennt, so dass das Kühlfluid weitgehend senkrecht auf die Innenwand der Turbinenschaufel gelangen kann. Damit wird eine sogenannte Prallkühlung erreicht. Diese ist effizient, da das Kühlfluid an der Innenwand verwirbelt wird und nach der Erwärmung wieder abströmt. Würde das Kühlfluid nur an der Innenwand der Turbinenschaufel vorbeiströmen, könnte sich ein unmittelbar an der Wand anliegender Film ausbilden, in dem die Strömung vergleichsweise schwach ist. Zudem würde in einem Bereich gerade erwärmtes Kühlfluid zur Kühlung anderer Bereiche genutzt.In one embodiment of the invention, the cooling channels are separated from an inner wall of the turbine blade by a perforated plate or a device in the manner of a perforated plate, so that the cooling fluid can pass largely perpendicular to the inner wall of the turbine blade. This achieves so-called impingement cooling. This is efficient because the cooling fluid is swirled on the inner wall and flows out again after the heating. If the cooling fluid only flow past the inner wall of the turbine blade, a film lying directly against the wall could form, in which the flow is comparatively weak. In addition, in one area just heated cooling fluid would be used to cool other areas.

In einer Ausführungsform der Erfindung beginnt mindestens ein Kühlkanal am Schaufelfuß in einem Bereich nahe der Eintrittskante der Turbinenschaufel. Der Einlass für das Kühlfluid liegt, auch bei den im Stand der Technik bekannten Anordnungen, aus konstruktiven Gründen regelmäßig am Schaufelfuß. Da an der Eintrittskante das die Turbinenschaufel antreibende Gasgemisch am heißesten ist, ist die thermische Belastung der Turbinenschaufel dort am höchsten. Daher ist es sinnvoll, dass ein Kühlkanal im Bereich der Eintrittskante beginnt.In one embodiment of the invention, at least one cooling passage begins at the blade root in a region near the leading edge of the turbine blade. The inlet for the cooling fluid is, even with the arrangements known in the prior art, for structural reasons regularly at the blade root. Since at the leading edge, the turbine blade driving gas mixture is hottest, the thermal load of the turbine blade is highest there. Therefore, it makes sense that a cooling duct begins in the area of the leading edge.

In einer weiteren Ausführungsform der Erfindung beginnt mindestens ein Kühlkanal in einem Bereich nahe der Eintrittskante und nahe des Schaufelfußes und führt als Diagonalkanal durch die Turbinenschaufel in einen Bereich nahe der Austrittskante und nahe der Schaufelblattspitze. Es ist dabei klarzustellen, dass der Diagonalkanal nicht am Schaufelfuß und nicht an der Eintrittskannte beginnen muss, sondern nur in diesem Bereich. Ein Beginn am Schaufelfuß und an der Eintrittskante soll aber nicht ausgeschlossen werden. Für das Ende des Diagonalkanals nahe der Austrittskante und nahe der Schaufelblattspitze gilt das Entsprechende. Der Diagonalkanal ermöglicht das Kühlfluid gut in verschiedene Bereiche der Turbinenschaufel zu führen und überall für eine effiziente Kühlung zu sorgen.In a further embodiment of the invention, at least one cooling channel begins in a region near the leading edge and near the blade root and leads as a diagonal channel through the turbine blade into a region near the trailing edge and near the blade tip. It should be made clear that the diagonal canal does not have to start at the blade root and not at the entrance but only in this area. A beginning at the blade root and at the leading edge but should not be excluded. The same applies to the end of the diagonal channel near the trailing edge and near the blade tip. The diagonal canal Allows the cooling fluid to flow well into different areas of the turbine blade and provide efficient cooling anywhere.

In einer weiteren Ausführungsform der Erfindung beginnen am Schaufelfuß in einem Bereich nahe der Eintrittskante zwei Kühlkanäle, die in einem Bereich nahe des Schaufelfußes enden und dort miteinander und mit dem Diagonalkanal verbunden sind. Damit kann Kühlfluid von Kühlfluideinlässen am Schaufelfuß zum Diagonalkanal gelangen. Sollte an einem der vorgenannten Kühlkanäle aufgrund eines Lecks Kühlfluid austreten, kann durch den anderen Kühlkanal der Diagonalkanal weiterhin mit Kühlfluid versorgt werden.In a further embodiment of the invention, two cooling channels begin at the blade root in a region near the leading edge, which end in a region near the blade root and are connected to one another and to the diagonal channel. This cooling fluid can pass from Kühlfluideinlässen the blade root to Diagonalkanal. If cooling fluid escapes from one of the aforementioned cooling channels due to a leak, the diagonal channel can continue to be supplied with cooling fluid through the other cooling channel.

In einer weiteren Ausführungsform der Erfindung zweigen vom Diagonalkanal weitere Kühlkanäle ab, wobei insbesondere Kühlkanäle in Richtung der Austrittskante abzweigen und/oder Kühlkanäle in Richtung der Schaufelblattspitze abzweigen. Auf diese Weise kann die Verteilung des Kühlfluids im gesamten Bereich der Turbinenschaufel weiter optimiert werden.In a further embodiment of the invention, further cooling channels branch off from the diagonal channel, wherein, in particular, cooling channels branch off in the direction of the outlet edge and / or branches off cooling channels in the direction of the blade blade tip. In this way, the distribution of the cooling fluid in the entire region of the turbine blade can be further optimized.

In einer weiteren Ausführungsform der Erfindung verläuft parallel zur Schaufelblattspitze ein Kühlkanal, in den die in Richtung der Schaufelblattspitze verlaufenden oben erwähnten Kühlkanäle münden. Der parallel zur Schaufelblattspitze verlaufende Kühlkanal kann dabei in denselben Bereich münden wie der Diagonalkanal.In a further embodiment of the invention, a cooling channel runs parallel to the blade tip, into which opening the above-mentioned cooling channels extending in the direction of the blade tip. The cooling channel running parallel to the blade tip can open into the same region as the diagonal channel.

In einer weiteren Ausführungsform der Erfindung verlaufen die in Richtung der Austrittskante abzweigenden Kühlkanäle weitgehend senkrecht zur Austrittskante. Alternativ oder ergänzend verlaufen die in Richtung der Schaufelblattspitze verlaufenden Kühlkanäle weitgehend parallel zur Austrittskante. Auch dies dient der weiteren Optimierung der Verteilung des Kühlfluids. Immer ist dabei im Blick, dass ein Leck an einer Stelle die Kühlung der Turbinenschaufel möglichst wenig beeinträchtigen soll.In a further embodiment of the invention, the cooling channels branching off in the direction of the outlet edge run largely perpendicular to the outlet edge. Alternatively or additionally, the cooling channels extending in the direction of the blade tip extend largely parallel to the outlet edge. This also serves to further optimize the distribution of the cooling fluid. It is always important to keep in mind that a leak at one point should affect the cooling of the turbine blade as little as possible.

In einer weiteren Ausführungsform der Erfindung sind im Bereich der Austrittskante Kühlfluidauslässe vorhanden, durch die Kühlfluid vom Bereich innerhalb der Turbinenschaufel in einen Bereich außerhalb der Turbinenschaufel gelangen kann. Damit kann im Bereich der Austrittskante auf einer Außenwand eine weitere Kühlung erreicht werden. Das ausgetretene Kühlfluid kann gegebenenfalls zum Antrieb einer weiteren Turbinenstufe genutzt werden.In a further embodiment of the invention, cooling fluid outlets are provided in the region of the outlet edge through which cooling fluid can pass from the region inside the turbine blade into an area outside the turbine blade. This can be achieved in the region of the trailing edge on an outer wall, a further cooling. The leaked cooling fluid can optionally be used to drive a further turbine stage.

In einer weiteren Ausführungsform der Erfindung ist am Schaufelfuß im Bereich der Austrittskante mindestens ein Kühlfluidauslass vorhanden. Das Kühlfluid kann vom Kühlfluideinlass, der normalerweise am Schaufelfuß im Bereich der Eintrittskante liegt, durch die Turbinenschaufel fließen und im Bereich der Austrittskante wieder zum Schaufelfuß strömen. Das austretende Kühlfluid kann zur Kühlung weiterer Turbinenschaufeln wieder verwendet werden.In a further embodiment of the invention, at least one cooling fluid outlet is provided on the blade root in the region of the outlet edge. The cooling fluid can flow from the cooling fluid inlet, which is normally located on the blade root in the region of the leading edge, through the turbine blade and flow back to the blade root in the area of the outlet edge. The exiting cooling fluid can be reused to cool additional turbine blades.

Anhand der Figur, die schematisch eine Anordnung von Kühlkanälen zeigt, soll die Erfindung nachfolgend anschaulicher dargestellt werden. Zu erkennen ist eine Anordnung 1 von Kühlkanälen in einer Gasturbinenschaufel. Wenngleich in der gewählten Ansicht aus Gründen der Übersichtlichkeit im Wesentlichen nur die Kühlkanäle zu erkennen sind, soll dennoch zunächst die Geometrie der Turbinenschaufel dargestellt werden, um den Verlauf der Kühlkanäle besser erläutern zu können.With reference to the figure, which shows schematically an arrangement of cooling channels, the invention will be illustrated below. Evident is an arrangement 1 of cooling channels in a gas turbine blade. Although in the selected view, for reasons of clarity, essentially only the cooling channels can be seen, the geometry of the turbine blade should nevertheless first be displayed in order to better explain the course of the cooling channels.

Unten liegt ein Schaufelfuß 2, mit dem die Turbinenschaufel an einem Rotor befestigt ist. Links ist eine Eintrittskante 3 zu erkennen. Die Eintrittskante 3 ist der Bereich, auf den ein die Turbinenschaufel antreibendes Gasgemisch zunächst auftrifft. Oben ist eine Schaufelblattspitze 4 zu erkennen. Rechts ist eine Austrittskante 5 angeordnet. Die Turbinenschaufel ist nicht eben, sondern gekrümmt. Dabei können die Eintrittskante 3 und die Austrittskante 5 gerade sein, aber auch gekrümmt verlaufen. Der Schaufelfuß 2 und die Schaufelblattspitze hingegen verlaufen wie auch der übrige Schaufelbereich in jedem Fall gekrümmt. Die Krümmung ist einer aerdodynamischen Form der Turbinenschaufel geschuldet.Below is a blade root 2, with which the turbine blade is attached to a rotor. On the left is an entrance edge 3 can be seen. The leading edge 3 is the area to which a gas mixture driving the turbine blade first impinges. Above a blade tip 4 can be seen. Right is a trailing edge 5 is arranged. The turbine blade is not flat, but curved. In this case, the leading edge 3 and the trailing edge 5 may be straight, but also curved. The blade root 2 and the blade tip, however, run as well as the rest of the blade area curved in any case. The curvature is due to an aerodynamic shape of the turbine blade.

Die Turbinenschaufel weist eine nicht dargestellte vordere Wand auf, die von der Eintrittskante zur Austrittskante verläuft und eine im Abstand davon verlaufende hintere Wand, welche wieder von der Austrittskante zur Eintrittskante führt. Im Allgemeinen ist der Abstand zwischen vorderer Wand und hinterer Wand im Bereich der Eintrittskante 3 und der Austrittskante 5 sehr niedrig und nimmt zur Schaufelmitte hin zu.The turbine blade has a front wall (not shown) extending from the leading edge to the trailing edge and a rear wall extending at a distance therefrom which again leads from the trailing edge to the leading edge. In general, the distance between the front wall and the rear wall in the region of the leading edge 3 and the trailing edge 5 is very low and increases toward the blade center.

Nun zur Anordnung der Kühlkanäle. Ein erster Kühlkanal 6 beginnt am Schaufelfuß 2 und verläuft direkt entlang der Eintrittskante 3. Auf der der Eintrittskante 3 abgewandten Seite des Kühlkanals 6 verläuft vom Schaufelfuß 2 weg ein weiterer Kühlkanal 7, der vom Kühlkanal 6 getrennt ist. Die Kühlkanäle 6 und 7 münden in einen Bereich 8, der nahe der Eintrittskante 3 und nahe dem Schaufelfuß 2 liegt. Dort sind die Kühlkanäle 6 und 7 miteinander verbunden. Im Bereich 8 beginnt ferner ein Diagonalkanal 9, der in einen Bereich 10 nahe der Austrittskante 5 und nahe der Schaufelblattspitze 4 führt. Vom Bereich 8 verläuft ein Kühlkanal 11 parallel zum Schaufelfuß 2. Der Kühlkanal 11 mündet in einen parallel zur Austrittskante 5 verlaufenden Kühlkanal 12. Folgt man dem Diagonalkanal 9 vom Bereich 8 nahe der Eintrittskante 3 zum Bereich 10 nahe der Austrittskante 5 zweigen zwei Kühlkanäle 13 und 14 ab, die parallel zum Kühlkanal 11 verlaufen und in den Kühlkanal 12 münden.Now for the arrangement of the cooling channels. A first cooling channel 6 begins at the blade root 2 and runs directly along the leading edge 3. On the side of the cooling channel 6 facing away from the leading edge 3, a further cooling channel 7 extends away from the blade root 2 and is separated from the cooling channel 6. The cooling channels 6 and 7 open into a region 8, which is near the leading edge 3 and near the blade root 2. There, the cooling channels 6 and 7 are interconnected. In the region 8, a diagonal channel 9, which leads into a region 10 near the trailing edge 5 and near the blade tip 4, also begins. From the region 8, a cooling channel 11 extends parallel to the blade root 2. The cooling channel 11 opens into a parallel to the trailing edge 5 extending cooling channel 12. If you follow the diagonal channel 9 from the area 8 near the leading edge 3 to the area 10 near the trailing edge 5 branches two cooling channels 13 and 14, which run parallel to the cooling channel 11 and open into the cooling channel 12.

Weiterhin zweigen zwei parallel zur Eintrittskante 3 verlaufende Kühlkanäle 15 und 16 vom Diagonalkanal 8 ab. Diese münden in einen Kühlkanal 17, der in der Nähe der Schaufelblattspitze 4 parallel zur Schaufelblattspitze 4 verläuft und in den Bereich 10 mündet und dort mit dem Diagonalkanal 9 verbunden ist. Der Bereich 10 ist darüber hinaus mit dem entlang der Austrittskante 5 verlaufenden Kühlkanal 12 verbunden. Der Kühlkanal 12 mündet im Schaufelfuß 2 in einen Kühlfluidauslass 18. Darüber hinaus sind Kühlfluidauslässe 19a bis 19g an der Austrittskante 5 vorhanden.Furthermore, two cooling channels 15 and 16 extending parallel to the leading edge 3 branch off from the diagonal channel 8. These lead into a cooling channel 17, which runs parallel to the blade tip 4 in the vicinity of the blade tip 4 and opens into the region 10 and is connected there to the diagonal channel 9. The region 10 is also connected to the cooling channel 12 running along the trailing edge 5. The cooling channel 12 opens in the blade root 2 in a cooling fluid outlet 18. In addition, cooling fluid outlets 19a to 19g are provided at the trailing edge 5.

Die Anordnung 1 der Kühlkanäle 6, 7, 9, 11, 12, 13, 14, 15, 16, 17 kann anschaulich auch als "Tannenbaumdesign" bezeichnet werden.The arrangement 1 of the cooling channels 6, 7, 9, 11, 12, 13, 14, 15, 16, 17 can also be referred to as "fir tree design".

Die Richtung der Strömung im Normalbetrieb, also bei Kühlung ohne dass ein Leck besteht, ist durch Pfeile dargestellt. Es wird deutlich, dass ein Leck an einem der vielen Kühlkanäle in aller Regel nur zu einer Einschränkung der Kühlung, nicht aber zum Ausfall der Kühlung führt.The direction of the flow in normal operation, ie cooling without a leak is shown by arrows. It becomes clear that a leak at one of the many cooling channels usually only leads to a restriction of the cooling, but not to the failure of the cooling.

Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen.Although the invention has been further illustrated and described in detail by the preferred embodiment, the invention is not limited by the disclosed examples, and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.

Claims (11)

Anordnung (1) von mehreren Kühlkanälen (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) innerhalb einer Turbinenschaufel zur Förderung von Kühlfluid,
wobei die Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) durch die Turbinenschaufel, welche einen Schaufelfuß (2), eine Schaufelblattspitze (4), eine Eintrittskante (3) und eine Austrittskante (5) aufweist, zu einem oder mehreren Kühlfluidauslässen (18, 19a-19g) führen,
wobei die Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) so an ausgewählten Stellen (8, 10) miteinander verbunden sind und in anderen Bereichen voneinander getrennt verlaufen, dass bei einer Beschädigung der Turbinenschaufel im Bereich eines Kühlkanals (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) die Kühlung durch die anderen Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) weitgehend unbeeinträchtigt bleibt.Arrangement (1) of a plurality of cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) within a turbine blade for conveying cooling fluid,
the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) being defined by the turbine blade, which has a blade root (2), a blade tip (4), an entry edge (3) and a discharge edge (3). 5) lead to one or more cooling fluid outlets (18, 19a-19g),
wherein the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) are connected to one another at selected locations (8, 10) and separated from each other in other areas such that the turbine blade is damaged in the region of a cooling channel (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) the cooling by the other cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) remains largely undisturbed. Anordnung (1) nach Anspruch 1,
dadurch gekennzeichnet, dass
die Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) so miteinander verbunden sind, dass bei Durchströmung der Anordnung (1) regelmäßig Kühlfluid von einem Kühlkanal (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) in einen anderen Kühlkanal (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) strömt.Arrangement (1) according to claim 1,
characterized in that
the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) are connected to one another in such a way that, when the arrangement (1) flows through, cooling fluid is regularly removed from a cooling channel (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) flows into another cooling channel (6, 7, 9, 11, 12, 13, 14, 15, 16, 17). Anordnung (1) nach einem der Ansprüche 1 oder 2,
dadurch gekennzeichnet, dass
die Kühlkanäle (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) von einer Innenwand der Turbinenschaufel durch ein Lochblech oder eine Vorrichtung nach Art eines Lochblechs getrennt sind, so dass das Kühlfluid weitgehend senkrecht auf die Innenwand der Turbinenschaufel gelangen kann.Arrangement (1) according to one of claims 1 or 2,
characterized in that
the cooling channels (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) are separated from an inner wall of the turbine blade by a perforated plate or a device in the manner of a perforated plate, so that the cooling fluid is substantially perpendicular to the inner wall the turbine blade can get. Anordnung (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
mindestens ein Kühlkanal (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) am Schaufelfuß (2) in einem Bereich nahe der Eintrittskante (3) beginnt.Arrangement (1) according to one of the preceding claims,
characterized in that
at least one cooling channel (6, 7, 9, 11, 12, 13, 14, 15, 16, 17) on the blade root (2) begins in a region near the leading edge (3). Anordnung (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
mindestens ein Kühlkanal in einem Bereich (8) nahe der Eintrittskante (3) und nahe des Schaufelfußes (2) beginnt und als Diagonalkanal (9) durch die Turbinenschaufel in einen Bereich (10) nahe der Austrittskante (5) und nahe der Schaufelblattspitze (4) führt.Arrangement (1) according to one of the preceding claims,
characterized in that
at least one cooling channel begins in a region (8) near the leading edge (3) and near the blade root (2) and as a diagonal channel (9) through the turbine blade into a region (10) near the trailing edge (5) and near the blade tip (4) ) leads. Anordnung (1) nach dem vorhergehenden Anspruch,
dadurch gekennzeichnet, dass
am Schaufelfuß (2) in einem Bereich nahe der Eintrittskante (3) zwei Kühlkanäle (6, 7) beginnen, die in einem Bereich (8) nahe des Schaufelfußes (2) enden und dabei miteinander und mit dem Diagonalkanal (9) verbunden sind.Arrangement (1) according to the preceding claim,
characterized in that
on the blade root (2) in a region near the leading edge (3) two cooling channels (6, 7) begin, which end in a region (8) near the blade root (2) and are connected to each other and to the diagonal channel (9). Anordnung (1) nach den beiden vorhergehenden Ansprüchen,
dadurch gekennzeichnet dass
vom Diagonalkanal (9) weitere Kühlkanäle (11, 13, 14, 15, 16) abzweigen, wobei insbesondere Kühlkanäle (11, 13, 14) in Richtung der Austrittskante (5) abzweigen und/oder Kühlkanäle (15, 16) in Richtung der Schaufelblattspitze (4) abzweigen.Arrangement (1) according to the two preceding claims,
characterized in that
branch off further cooling channels (11, 13, 14, 15, 16) from the diagonal channel (9), wherein in particular cooling channels (11, 13, 14) branch off in the direction of the outlet edge (5) and / or cooling channels (15, 16) in the direction of Branch the blade tip (4). Anordnung nach dem vorhergehenden Anspruch,
dadurch gekennzeichnet, dass
parallel zur Schaufelblattspitze (4) ein Kühlkanal verläuft, in den die in Richtung der Schaufelblattspitze (4) verlaufenden Kühlkanäle (15, 16) münden.Arrangement according to the preceding claim,
characterized in that
parallel to the blade tip (4) extends a cooling channel, in which in the direction of the blade tip (4) extending cooling channels (15, 16) open. Anordnung (1) nach den beiden vorhergehenden Ansprüchen,
dadurch gekennzeichnet, dass
die in Richtung der Austrittskante (5) abzweigenden Kühlkanäle (11, 13, 14) weitgehend senkrecht zur Austrittskante (5) verlaufen und/oder die in Richtung der Schaufelblattspitze (4) verlaufenden Kühlkanäle (15, 16) weitgehend parallel zur Austrittskante (5) verlaufen.Arrangement (1) according to the two preceding claims,
characterized in that
the cooling channels (11, 13, 14) branching off in the direction of the outlet edge (5) run largely perpendicular to the outlet edge (5) and / or the cooling channels (15, 16) running in the direction of the blade tip (4) are substantially parallel to the outlet edge (5) run. Anordnung (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
im Bereich der Austrittskante (5) Kühlfluidauslässe (19a-19g) vorhanden sind, bei denen Kühlfluid vom Bereich innerhalb der Turbinenschaufel in einen Bereich außerhalb der Turbinenschaufel gelangen kann.Arrangement (1) according to one of the preceding claims,
characterized in that
cooling fluid outlets (19a-19g) are provided in the region of the outlet edge (5), in which cooling fluid can pass from the region inside the turbine blade into an area outside the turbine blade. Anordnung (1) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass
am Schaufelfuß (2) im Bereich der Austrittskante (5) mindestens ein Kühlfluidauslass (18) vorhanden ist.Arrangement (1) according to one of the preceding claims,
characterized in that
At least one cooling fluid outlet (18) is provided on the blade root (2) in the region of the outlet edge (5).
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JP2016516886A JP2016533446A (en) 2013-09-25 2014-09-17 Arrangement of cooling channels in turbine blades
PCT/EP2014/069747 WO2015044007A1 (en) 2013-09-25 2014-09-17 Arrangement of cooling channels in a turbine blade
EP14772098.1A EP3022397A1 (en) 2013-09-25 2014-09-17 Arrangement of cooling channels in a turbine blade
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180291743A1 (en) * 2017-04-07 2018-10-11 General Electric Company Turbine engine airfoil having a cooling circuit

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3037830B1 (en) * 2015-06-29 2024-02-16 Snecma MOLDING ASSEMBLY FOR A TURBOMACHINE BLADE, INCLUDING A LARGE SECTION RELIEF PORTION
US10544684B2 (en) * 2016-06-29 2020-01-28 General Electric Company Interior cooling configurations for turbine rotor blades
FR3057906B1 (en) * 2016-10-20 2019-03-15 Safran Aircraft Engines OPTIMIZED COOLING TURBINE TANK
US10422229B2 (en) * 2017-03-21 2019-09-24 United Technologies Corporation Airfoil cooling
US11644046B2 (en) * 2018-01-05 2023-05-09 Aurora Flight Sciences Corporation Composite fan blades with integral attachment mechanism
EP3832069A1 (en) * 2019-12-06 2021-06-09 Siemens Aktiengesellschaft Turbine blade for a stationary gas turbine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB827289A (en) * 1955-10-26 1960-02-03 Wiggin & Co Ltd Henry Improvements relating to hollow turbine or compressor blades
FR1209752A (en) * 1958-09-10 1960-03-03 Wiggin & Co Ltd Henry Improvements in the manufacture of turbine blades and similar machines
US3014693A (en) * 1957-06-07 1961-12-26 Int Nickel Co Turbine and compressor blades
JPS59231103A (en) * 1983-06-14 1984-12-25 Toshiba Corp Cooled blade of gas turbine
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
EP0939196A2 (en) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Gas turbine blade
US6382914B1 (en) * 2001-02-23 2002-05-07 General Electric Company Cooling medium transfer passageways in radial cooled turbine blades
EP1471210A1 (en) * 2003-04-24 2004-10-27 Siemens Aktiengesellschaft Turbine component with impingement cooling plate
US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641439A (en) * 1947-10-01 1953-06-09 Chrysler Corp Cooled turbine or compressor blade
US2687278A (en) * 1948-05-26 1954-08-24 Chrysler Corp Article with passages
DE1097212B (en) * 1956-10-22 1961-01-12 Her Majesty The Queen In The R Blade provided with cooling ducts, especially for gas turbines
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3171631A (en) * 1962-12-05 1965-03-02 Gen Motors Corp Turbine blade
US3554663A (en) * 1968-09-25 1971-01-12 Gen Motors Corp Cooled blade
JPS6285102A (en) * 1985-10-11 1987-04-18 Hitachi Ltd Gas turbine cooling blade
JP2851575B2 (en) * 1996-01-29 1999-01-27 三菱重工業株式会社 Steam cooling wings
EP2378073A1 (en) * 2010-04-14 2011-10-19 Siemens Aktiengesellschaft Blade or vane for a turbomachine
CN201991570U (en) * 2011-03-11 2011-09-28 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Turbine rotor blade of gas turbine
US9528379B2 (en) * 2013-10-23 2016-12-27 General Electric Company Turbine bucket having serpentine core

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB827289A (en) * 1955-10-26 1960-02-03 Wiggin & Co Ltd Henry Improvements relating to hollow turbine or compressor blades
US3014693A (en) * 1957-06-07 1961-12-26 Int Nickel Co Turbine and compressor blades
FR1209752A (en) * 1958-09-10 1960-03-03 Wiggin & Co Ltd Henry Improvements in the manufacture of turbine blades and similar machines
JPS59231103A (en) * 1983-06-14 1984-12-25 Toshiba Corp Cooled blade of gas turbine
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
EP0939196A2 (en) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Gas turbine blade
US6382914B1 (en) * 2001-02-23 2002-05-07 General Electric Company Cooling medium transfer passageways in radial cooled turbine blades
EP1471210A1 (en) * 2003-04-24 2004-10-27 Siemens Aktiengesellschaft Turbine component with impingement cooling plate
US20050084370A1 (en) * 2003-07-29 2005-04-21 Heinz-Jurgen Gross Cooled turbine blade

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180291743A1 (en) * 2017-04-07 2018-10-11 General Electric Company Turbine engine airfoil having a cooling circuit
US10697301B2 (en) * 2017-04-07 2020-06-30 General Electric Company Turbine engine airfoil having a cooling circuit

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EP3022397A1 (en) 2016-05-25

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