EP1138878B1 - Gas turbine component - Google Patents

Gas turbine component Download PDF

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Publication number
EP1138878B1
EP1138878B1 EP01108008A EP01108008A EP1138878B1 EP 1138878 B1 EP1138878 B1 EP 1138878B1 EP 01108008 A EP01108008 A EP 01108008A EP 01108008 A EP01108008 A EP 01108008A EP 1138878 B1 EP1138878 B1 EP 1138878B1
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EP
European Patent Office
Prior art keywords
plenum
cooling
component
component according
hot gas
Prior art date
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EP01108008A
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German (de)
French (fr)
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EP1138878A2 (en
EP1138878A3 (en
Inventor
Alexander Dr. Beeck
Christoph Nagler
Mark Richter
Klaus Semmler
Lothar Schneider
Joerg Dr. Stengele
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General Electric Technology GmbH
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Alstom Technology AG
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Publication of EP1138878A3 publication Critical patent/EP1138878A3/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/103—Multipart cores
    • 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
    • F01D5/187—Convection 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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 a component of a gas turbine with a plate-shaped, projecting component section according to the preamble of claim 1.
  • Plate-shaped projecting component sections are often found in gas turbines where, for structural reasons, overhanging areas of main components, such as blades, fasteners are provided or sealing elements, even between two adjacent components, must be attached. Such overhanging component sections are problematic, especially in areas subject to high thermal stress, in which hot gas is applied to the surface. There it is often necessary to provide cooling.
  • a cooled turbine gas turbine blade in which overhanging regions are formed in the form of plate-shaped cantilevered component sections which are mounted in the axial direction in front of and behind the blade root to ensure coverage in the hub region with the adjacently arranged blade root regions of rotor blades.
  • cooling holes are provided, which are flowed through by convection cooling air.
  • the cooling holes extend, for example, in the front overhanging component portion in the circumferential direction and are fed by the main cooling air supply. Due to the high thermal load in this area, turbulence generators are additionally present in the cooling bores in order to improve the heat transfer.
  • the rear, overhanging component portion has a plurality of axially extending cooling holes, which are also fed by the main cooling air supply.
  • the cooling holes open axially at the downstream end of the component section, so that the cooling medium emerges into the hot gas stream after flowing through the cooling channels.
  • the trailing edge cavity of the blade platform has a plurality of film cooling passages which ensure film cooling of the blade trailing edge.
  • the trailing edge cavity is produced in a casting process using a ceramic core.
  • the concerns US 5460486 A a turbine blade of a gas turbine with at least one extending in the blade cooling air duct, and arranged at the blade tip shroud segment, which forms a blade reinforcing band together with other segments of adjacent blades, and with a in the shroud segment substantially vertical to the blade axis and running with the cooling air passage channel connected to the blade cooling air channel located in the blade inflow region, from which cooling air holes lead to the surface of the shroud segment.
  • a film cooling is provided in this solution, wherein the film cooling holes are arranged downstream of the component edge (sealing edge) of the shroud segment relative to the flow direction of the hot gas.
  • the invention seeks to avoid the disadvantages described. It is the object of the invention to provide a component of a gas turbine with a plate-shaped, projecting component portion of the type mentioned, which allows more effective cooling of the surface acted upon by hot gas and thus has an increased life with reduced cooling air requirement.
  • the plenum in the form of at least one first cooling hole opens at the axial downstream end of the component portion.
  • a number of preferred embodiments is directed to the simple and cost-effective implementation of this cooling concept.
  • the choice of the optimum shaping process for the plenum depends mainly on the manufacturing process of the actual component, on which the plate-shaped projecting portion is provided. Other important aspects are the geometry to be realized, as well as the manufacturing specifications.
  • a multi-part core is used to realize the desired geometry of the plenum.
  • lateral openings for positioning the core may be required, which can be closed subsequently, that is, following the molding process.
  • the plenum is connected via feed channels with a Weinplenum, which supplies the blade with cooling air.
  • a Weinplenum which supplies the blade with cooling air.
  • the above-described cooling concept can be implemented for use in any desired, thermally highly stressed components of a gas turbine, it is preferably used on overhangs of turbine blades.
  • the thermal loads are particularly high, on the other hand, in the immediate vicinity of the overhang usually provided a coolant supply anyway, which can be particularly easy to implement the cooling concept of the invention.
  • plenum 10 In the in the Fig. 1 and Fig. 2 illustrated embodiment, four substantially parallel and spaced apart plenum 10 are provided on the overhang 1, which consistently pass through the overhang 1 and open in the form of first cooling holes at the axial downstream end of the component section.
  • the plenums run directly adjacent to the surface 2 and cool them in this area by a not shown in detail, convective pass cooling medium.
  • second cooling bores 12 are provided, preferably arranged in rows and in association with the plenums 10. They emanate from the plenum 10 and open into vent openings 13 at the surface 2, upstream of the axial downstream end of the overhang. In this way, cooling medium is blown out of the plenum 10 through the blow-out openings 13 in such a way that a coherent cooling film is formed.
  • the surface 2 is optimally cooled.
  • the plenums 10 may be formed by EDM tools 19 which drill through holes in the overhang 1. It is thus made a connection to a Hauptplenum 5 below the platform 3, whereby the Pleni 10 are fed with cooling air from this area.
  • the cross section of the individual plenums 10 may vary to achieve a cooling effect tailored to the local heat load. This also applies with regard to their number and distribution of their arrangement along the overhang 1. The same applies mutatis mutandis to the cooling holes or outlet openings 12, which are responsible for the formation of the cooling film.
  • Fig. 3 illustrated embodiment shows a plenum 30, which passes through the overhang 1 with respect to its longitudinal and transverse extent largely completely. This allows a largely ideal uniformed convective cooling of the surface 2 and also offers the possibility to arrange the (not shown here) film cooling air holes in any distributed.
  • Feed channels 6 are provided for this purpose, which establish the connection between the main plenum 5 and the plenum 30.
  • the plenum 30 and the feed channels 6 are in this case formed directly during the casting process.
  • a in Fig. 4 shown core 39, which dictates the shape of the plenum 30.
  • two feed channel sections 38 are provided to form the feed channels 6.
  • 39 can be formed in a simple manner, the plenum 30 including the feed channels 6.
  • the above-described concept is not limited to the application to overhangs of turbine blades, but an application is possible wherever plate-shaped cantilevered component sections are exposed to high thermal loads and therefore must be effectively cooled.

Description

Technisches GebietTechnical area

Die Erfindung betrifft ein Bauteil einer Gasturbine mit einem plattenförmigen, auskragenden Bauteilabschnitt gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a component of a gas turbine with a plate-shaped, projecting component section according to the preamble of claim 1.

Stand der TechnikState of the art

Plattenförmig auskragende Bauteilabschnitte sind bei Gasturbinen häufig dort anzutreffen, wo aus konstruktiven Gründen überhängende Bereiche an Hauptbauteilen, wie beispielsweise an Schaufeln, Befestigungselemente vorzusehen sind oder Dichtungselemente, auch zwischen zwei benachbarten Bauteilen, angebracht werden müssen. Problematisch sind derartige überhängende Bauteilabschnitte speziell in thermisch hochbelasteten Bereichen, in denen die Oberfläche mit Heißgas beaufschlagt wird. Dort ist es vielfach unerlässlich, eine Kühlung vorzusehen.Plate-shaped projecting component sections are often found in gas turbines where, for structural reasons, overhanging areas of main components, such as blades, fasteners are provided or sealing elements, even between two adjacent components, must be attached. Such overhanging component sections are problematic, especially in areas subject to high thermal stress, in which hot gas is applied to the surface. There it is often necessary to provide cooling.

Aus der EP 0 911 486 A2 ist eine gekühlte Schaufel einer Gasturbine bekannt, bei der überhängende Bereiche in Form plattenförmiger, auskragender Bauteilabschnitte gebildet sind, die in axialer Richtung vor und hinter dem Schaufelfuß angebracht sind, um im Nabenbereich eine Überdeckung mit den benachbart angeordneten Schaufelfußbereichen von Rotorschaufeln zu gewährleisten. Zur Kühlung dieser plattenförmigen, auskragenden Bauteilabschnitte sind Kühlbohrungen vorgesehen, die von Kühlluft rein konvektiv durchströmt werden. Die Kühlbohrungen verlaufen beispielsweise im vorderen überhängenden Bauteilabschnitt in Umfangsrichtung und werden von der Haupt-Kühlluftversorgung gespeist. Aufgrund der hohen thermischen Belastung in diesem Bereich sind in den Kühlbohrungen zusätzlich Turbulenzerzeuger vorhanden, um den Wärmeübergang zu verbessern.From the EP 0 911 486 A2 a cooled turbine gas turbine blade is known, in which overhanging regions are formed in the form of plate-shaped cantilevered component sections which are mounted in the axial direction in front of and behind the blade root to ensure coverage in the hub region with the adjacently arranged blade root regions of rotor blades. For cooling these plate-shaped, projecting component sections cooling holes are provided, which are flowed through by convection cooling air. The cooling holes extend, for example, in the front overhanging component portion in the circumferential direction and are fed by the main cooling air supply. Due to the high thermal load in this area, turbulence generators are additionally present in the cooling bores in order to improve the heat transfer.

Der hintere, überhängende Bauteilabschnitt weist eine Vielzahl axial verlaufender Kühlbohrungen auf, die ebenfalls von der Haupt-Kühlluftversorgung gespeist werden. Die Kühlbohrungen münden axial am stromabwärtigen Ende des Bauteilabschnittes, so dass das Kühlmedium nach Durchströmen der Kühlkanäle in den Heißgasstrom austritt.The rear, overhanging component portion has a plurality of axially extending cooling holes, which are also fed by the main cooling air supply. The cooling holes open axially at the downstream end of the component section, so that the cooling medium emerges into the hot gas stream after flowing through the cooling channels.

Beiden Bauteilabschnitten ist gemeinsam, dass die vom Heißgas beaufschlagte Oberfläche rein konvektiv gekühlt wird. Nachteilig ist hierbei, dass sehr viel Kühlluft aufgewendet werden muss, um die erforderliche Kühlwirkung zu erzielen. Dies hat eine Verschlechterung des Gesamtwirkungsgrades zur Folge oder macht den Einsatz teurer hochtemperaturbeständiger Materialien erforderlich.Both component sections have in common that the surface acted upon by the hot gas is cooled purely convectively. The disadvantage here is that a lot of cooling air must be expended in order to achieve the required cooling effect. This results in a deterioration of the overall efficiency or makes the use of expensive high temperature resistant materials required.

Weiterhin ist aus der US 5413458 A eine Turbinenleitschaufel mit einer Kühlluftversorgung des Deckbandes bekannt. Bei dieser Lösung weist der Hinterkantenhohlraum der Schaufelplattform mehrere Filmkühlpassagen auf, welche eine Filmkühlung der Schaufelhinterkante gewährleisten. Der Hinterkantenhohlraum wird in einem Gussprozess mit Hilfe eines Keramikkerns hergestellt.Furthermore, from the US 5413458 A a turbine vane with a cooling air supply of the shroud known. In this solution, the trailing edge cavity of the blade platform has a plurality of film cooling passages which ensure film cooling of the blade trailing edge. The trailing edge cavity is produced in a casting process using a ceramic core.

Schließlich betrifft die US 5460486 A eine Turbinenschaufel einer Gasturbine mit zumindest einem in der Schaufel verlaufenden Kühlluftkanal, sowie mit einem an der Schaufelspitze angeordneten Deckband-Segment, das gemeinsam mit weiteren Segmenten benachbarter Schaufeln ein Schaufelverstärkungsband bildet, sowie mit einem im Deckband-Segment im wesentlichen vertikal zur Schaufelachse verlaufenden und mit dem im Schaufel-Anströmbereich liegenden Schaufel Kühlluftkanal verbundenen Kühlluft-Stichkanal, von dem aus Kühlluft-Bohrungen zur Oberfläche des Deckband-Segmentes führen. Neben einer Konvektionskühlung ist bei dieser Lösung auch eine Filmkühlung vorgesehen, wobei deren Filmkühllöcher bezogen auf die Strömungsrichtung des Heißgases stromab der Bauteilkante (Dichtkante) des Deckband-Segmentes angeordnet sind.Finally, the concerns US 5460486 A a turbine blade of a gas turbine with at least one extending in the blade cooling air duct, and arranged at the blade tip shroud segment, which forms a blade reinforcing band together with other segments of adjacent blades, and with a in the shroud segment substantially vertical to the blade axis and running with the cooling air passage channel connected to the blade cooling air channel located in the blade inflow region, from which cooling air holes lead to the surface of the shroud segment. In addition to a convection cooling a film cooling is provided in this solution, wherein the film cooling holes are arranged downstream of the component edge (sealing edge) of the shroud segment relative to the flow direction of the hot gas.

Darstellung der ErfindungPresentation of the invention

Die Erfindung versucht, die beschriebenen Nachteile zu vermeiden. Ihr liegt die Aufgabe zugrunde, ein Bauteil einer Gasturbine mit einem plattenförmigen, auskragenden Bauteilabschnitt der eingangs genannten Art anzugeben, das eine effektivere Kühlung der von Heißgas beaufschlagten Oberfläche ermöglicht und somit eine erhöhte Lebensdauer bei gleichzeitig verringertem Kühlluftbedarf aufweist.The invention seeks to avoid the disadvantages described. It is the object of the invention to provide a component of a gas turbine with a plate-shaped, projecting component portion of the type mentioned, which allows more effective cooling of the surface acted upon by hot gas and thus has an increased life with reduced cooling air requirement.

Erfindungsgemäß wird dies dadurch erreicht, dass bei einem Bauteil gemäß dem Oberbegriff des Anspruchs 1 das Plenum in Form von wenigstens einer ersten Kühlbohrung am axialen stromabwärtigen Ende des Bauteilabschnittes mündet. Zudem gehen vom Plenum zweite Kühlbohrungen aus, welche Ausblaseöffnungen aufweisen und-stromauf des axialen stromabwärtigen Endes des Bauteilabschnittes an der von Heißgas beaufschlagten Oberfläche münden, wodurch ein Kühlfilm generierbar ist.According to the invention this is achieved in that in a component according to the preamble of claim 1, the plenum in the form of at least one first cooling hole opens at the axial downstream end of the component portion. In addition, go from the plenum second cooling holes, which have blow-off and-open upstream of the axial downstream end of the component portion of the acted upon by hot gas surface, whereby a cooling film can be generated.

Somit ist es möglich, eine höchst effektive Filmkühlung an der von Heißgas beaufschlagten Oberfläche zu realisieren, wobei der Kühlmittelverbrauch äußerst gering gehalten werden kann. Der Grund liegt darin, dass die Kühlluft zunächst konvektiv den zu kühlenden Bereich durchströmt, um anschließend durch Ausblasung einen hocheffektiven Kühlfilm auszubilden.Thus, it is possible to realize a highly effective film cooling on the surface acted upon by hot gas, wherein the coolant consumption can be kept extremely low. The reason is that the cooling air first flows convectively through the area to be cooled in order to then form a highly effective cooling film by blowing it out.

Obwohl grundsätzlich weitgehende Gestaltungsfreiheit hinsichtlich der Ausgestaltung des Plenums besteht, hat es sich als vorteilhaft erwiesen, wenn ein einziges, durchgehendes Plenum vorgesehen ist, das den Bauteilabschnitt weitgehend vollständig durchsetzt. Auf diese Weise wird die von Heißgas beaufschlagte Oberfläche gleichmäßig und ohne örtliche Unterbrechung durch beispielsweise Zwischenwände gekühlt, wodurch eine bislang unerreicht effektive Kühlwirkung realisierbar ist.Although in principle extensive freedom of design exists with regard to the design of the plenum, it has proved to be advantageous if a single, continuous plenum is provided, which largely completely penetrates the component section. In this way, the acted upon by hot gas surface is cooled evenly and without local interruption, for example by intermediate walls, whereby a hitherto unachieved effective cooling effect can be realized.

Eine Reihe bevorzugter Ausführungsvarianten ist auf die einfache und kostengünstige Realisierung dieses Kühlkonzepts gerichtet. Die Wahl des optimalen Formgebungsprozesses für das Plenum hängt in der Hauptsache vom Herstellverfahren des eigentlichen Bauteils ab, an dem der plattenförmige, auskragende Abschnitt vorzusehen ist. Weitere wichtige Gesichtspunkte sind die zu realisierende Geometrie, sowie die fertigungstechnischen Vorgaben.A number of preferred embodiments is directed to the simple and cost-effective implementation of this cooling concept. The choice of the optimum shaping process for the plenum depends mainly on the manufacturing process of the actual component, on which the plate-shaped projecting portion is provided. Other important aspects are the geometry to be realized, as well as the manufacturing specifications.

Im Falle der häufig anzutreffenden Überhänge an Turbinenschaufeln bietet es sich an, das Plenum unmittelbar bei der Formgebung im Gießverfahren mitzuformen. Dies ist in der Regel ohne großen Zusatzaufwand möglich, wobei nach dem Entformen das Plenum unmittelbar und ohne Notwendigkeit einer Nachbearbeitung gebildet ist.In the case of the frequently encountered overhangs on turbine blades, it is advisable to co-form the plenum directly during shaping in the casting process. This is usually possible without much additional effort, after demolding the plenum is formed directly and without the need for reworking.

In der Regel wird ein mehrteiliger Kern verwendet, um die gewünschte Geometrie des Plenums zu realisieren. Gegebenenfalls können seitliche Durchbrüche zur Positionierung des Kerns erforderlich werden, die nachträglich, das heißt im Anschluss an das Formgebungsverfahren geschlossen werden können.In general, a multi-part core is used to realize the desired geometry of the plenum. Optionally, lateral openings for positioning the core may be required, which can be closed subsequently, that is, following the molding process.

Schließlich ist es auch möglich, sowohl das Plenum als auch die Ausblasöffnungen mittels EDM-Verfahren herzustellen. Mit Hilfe dieses Verfahrens lassen sich insbesondere Form, Größe und Anordnung der Ausblasöffnungen frei wählen und mit höchster Präzision umsetzen. Auch kann das Plenum als solches mit diesem Verfahren exakt umgesetzt werden.Finally, it is also possible to produce both the plenum and the blow-out openings by means of EDM processes. With the help of this method, in particular shape, size and arrangement of the exhaust ports can be freely selected and implemented with the utmost precision. Also, the plenum as such can be accurately implemented with this method.

Bevorzugt ist das Plenum über Speisekanäle mit einem Hauptplenum verbunden, welches die Schaufel mit Kühlluft versorgt. Auf diese Weise ist kein direkter Anschluss an die Kühlmediumversorgung erforderlich, wodurch sich der konstruktive Aufwand reduzieren lässt.Preferably, the plenum is connected via feed channels with a Hauptplenum, which supplies the blade with cooling air. In this way, no direct connection to the cooling medium supply is required, which can reduce the design effort.

Obwohl sich das vorstehend beschriebene Kühlkonzept zur Anwendung bei an sich beliebigen, thermisch hochbelasteten Bauteilen einer Gasturbine realisieren lässt, wird es bevorzugt an Überhängen von Turbinenschaufeln eingesetzt. Dort sind einerseits die thermischen Belastungen besonders hoch, andererseits ist in unmittelbarer Nachbarschaft des Überhangs meist ohnehin eine Kühlmittelversorgung vorgesehen, wodurch sich das erfindungsgemäße Kühlkonzept besonders einfach umsetzen lässt.Although the above-described cooling concept can be implemented for use in any desired, thermally highly stressed components of a gas turbine, it is preferably used on overhangs of turbine blades. There, on the one hand, the thermal loads are particularly high, on the other hand, in the immediate vicinity of the overhang usually provided a coolant supply anyway, which can be particularly easy to implement the cooling concept of the invention.

Kurze Beschreibung der ZeichnungShort description of the drawing

Es sind Ausführungsbeispiele der Erfindung schematisch dargestellt. Es zeigen:

Fig. 1
Überhang an einer Turbinenschaufel, perspektivische Ansicht von oben;
Fig. 2
Überhang gemäß Fig. 1, Ansicht von unten;
Fig. 3
Überhang an einer Turbinenschaufel gemäß einer ersten Ausführungsvariante, Ansicht von unten;
Fig.4
Kern zur Herstellung eines Plenums;
Embodiments of the invention are shown schematically. Show it:
Fig. 1
Overhang on a turbine blade, perspective view from above;
Fig. 2
Overhang according to Fig. 1 , Bottom view;
Fig. 3
Overhang on a turbine blade according to a first embodiment, view from below;
Figure 4
Core for making a plenum;

Es sind lediglich die für das Verständnis der Erfindung wesentlichen Elemente gezeigt und beschrieben.Only the essential elements for understanding the invention are shown and described.

Weg zur Ausführung der ErfindungWay to carry out the invention

Das erfindungsgemäße Konzept wird anhand eines plattenförmigen, auskragenden Bauteilabschnitts in Form eines Überhangs 1 erläutert, der als Bestandteil einer eine Turbinenschaufel 4 tragenden Plattform 3 gebildet ist. Eine Oberfläche 2 wird hierbei thermisch hoch belastet, nämlich durch einen hier nicht dargestellten Heißgasstrahl. Insoweit sind die nachstehend näher beschriebenen Ausführungsvarianten übereinstimmend gestaltet.The inventive concept is explained on the basis of a plate-shaped projecting component section in the form of an overhang 1, which is formed as part of a turbine blade 4 supporting platform 3. A surface 2 is in this case subjected to high thermal loads, namely by a hot gas jet, not shown here. In that regard, the embodiments described in more detail below are designed consistently.

Bei dem in den Fig. 1 und Fig. 2 dargestellten Ausführungsbeispiel sind am Überhang 1 vier im Wesentlichen parallel und beabstandet zueinander angeordnete Pleni 10 vorhanden, die durchgängig den Überhang 1 durchsetzen und in Form von ersten Kühlbohrungen am axialen stromabwärtigen Ende des Bauteilabschnittes münden. Die Pleni verlaufen unmittelbar benachbart zur Oberfläche 2 und kühlen diese in diesem Bereich durch ein nicht näher dargestelltes, konvektiv hindurchgeleitetes Kühlmedium. Weiterhin sind zweite Kühlbohrungen 12 vorhanden, und zwar bevorzugt zu Reihen und in Zuordnung zu den Pleni 10 angeordnet. Sie gehen von den Pleni 10 aus und münden in Ausblaseöffnungen 13 an der Oberfläche 2, stromauf des axialen stromabwärtigen Endes des Überhangs. Auf diese Weise wird Kühlmedium aus den Pleni 10 durch die Ausblaseöffnungen 13 derart ausgeblasen, dass sich ein zusammenhängender Kühlfilm ausbildet. Somit wird die Oberfläche 2 optimal gekühlt.In the in the Fig. 1 and Fig. 2 illustrated embodiment, four substantially parallel and spaced apart plenum 10 are provided on the overhang 1, which consistently pass through the overhang 1 and open in the form of first cooling holes at the axial downstream end of the component section. The plenums run directly adjacent to the surface 2 and cool them in this area by a not shown in detail, convective pass cooling medium. Furthermore, second cooling bores 12 are provided, preferably arranged in rows and in association with the plenums 10. They emanate from the plenum 10 and open into vent openings 13 at the surface 2, upstream of the axial downstream end of the overhang. In this way, cooling medium is blown out of the plenum 10 through the blow-out openings 13 in such a way that a coherent cooling film is formed. Thus, the surface 2 is optimally cooled.

Wie sich insbesondere aus Fig. 2 ergibt, können die Pleni 10 durch EDM-Werkzeuge 19 gebildet werden, die Durchgangsöffnungen in den Überhang 1 bohren. Es wird damit eine Verbindung zu einem Hauptplenum 5 unterhalb der Plattform 3 hergestellt, wodurch die Pleni 10 mit Kühlluft aus diesem Bereich gespeist werden.As can be seen in particular Fig. 2 As a result, the plenums 10 may be formed by EDM tools 19 which drill through holes in the overhang 1. It is thus made a connection to a Hauptplenum 5 below the platform 3, whereby the Pleni 10 are fed with cooling air from this area.

Der Querschnitt der einzelnen Pleni 10 kann variieren, um eine auf die lokale Wärmebelastung abgestimmte Kühlwirkung zu erzielen. Dies gilt auch hinsichtlich ihrer Anzahl und Verteilung ihrer Anordnung längs des Überhangs 1. Gleiches gilt sinngemäß für die Kühlbohrungen bzw. Ausblaseöffnungen 12, die für die Ausbildung des Kühlfilms verantwortlich sind.The cross section of the individual plenums 10 may vary to achieve a cooling effect tailored to the local heat load. This also applies with regard to their number and distribution of their arrangement along the overhang 1. The same applies mutatis mutandis to the cooling holes or outlet openings 12, which are responsible for the formation of the cooling film.

Die in Fig. 3 dargestellte Ausführungsvariante zeigt ein Plenum 30, das den Überhang 1 hinsichtlich seiner Längs- und Quererstreckung weitgehend vollständig durchgehend durchsetzt. Dies ermöglicht eine weitgehend ideal vergleichmäßigte konvektive Kühlung der Oberfläche 2 und bietet darüber hinaus die Möglichkeit, die (hier nicht näher dargestellten) Film-Kühlluftbohrungen an sich beliebig verteilt anzuordnen.In the Fig. 3 illustrated embodiment shows a plenum 30, which passes through the overhang 1 with respect to its longitudinal and transverse extent largely completely. This allows a largely ideal uniformed convective cooling of the surface 2 and also offers the possibility to arrange the (not shown here) film cooling air holes in any distributed.

Wiederum wird das Plenum 30 vom Hauptplenum 5 versorgt. Hierzu sind Speisekanäle 6 vorgesehen, die die Verbindung zwischen dem Hauptplenum 5 und dem Plenum 30 herstellen.Again, the plenum 30 is powered by the main plenum 5. Feed channels 6 are provided for this purpose, which establish the connection between the main plenum 5 and the plenum 30.

Das Plenum 30 und die Speisekanäle 6 sind in diesem Fall direkt während des Gießvorganges gebildet. Hierzu wird ein in Fig. 4 dargestellter Kern 39 verwendet, der die Form des Plenums 30 vorgibt. Weiterhin sind zwei Speisekanalabschnitte 38 vorgesehen, um die Speisekanäle 6 zu bilden. Mit Hilfe dieses mehrteiligen Kerns 38, 39 lässt sich auf einfache Art und Weise das Plenum 30 einschließlich der Speisekanäle 6 formen.The plenum 30 and the feed channels 6 are in this case formed directly during the casting process. For this purpose, a in Fig. 4 shown core 39, which dictates the shape of the plenum 30. Furthermore, two feed channel sections 38 are provided to form the feed channels 6. With the help of this multi-part core 38, 39 can be formed in a simple manner, the plenum 30 including the feed channels 6.

Wie bereits eingangs erwähnt, ist das vorstehend beschriebene Konzept nicht nur auf die Anwendung an Überhängen von Turbinenschaufeln beschränkt, vielmehr ist eine Anwendung überall dort möglich, wo plattenförmige, auskragende Bauteilabschnitte hohen thermischen Belastungen ausgesetzt sind und demzufolge effektiv gekühlt werden müssen.As already mentioned, the above-described concept is not limited to the application to overhangs of turbine blades, but an application is possible wherever plate-shaped cantilevered component sections are exposed to high thermal loads and therefore must be effectively cooled.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Überhangoverhang
22
Heißgasseitige OberflächeHot gas side surface
33
Plattformplatform
44
Turbinenschaufelturbine blade
55
Hauptplenummain plenary
66
Speisekanalfeeding channel
1010
Plenum, EDM-BohrungPlenum, EDM drilling
1212
Film-KühlbohrungFilm cooling hole
1313
Ausblaseöffnungblowoff
1919
EDM-WerkzeugEDM tool
3030
Plenumplenum
3838
SpeisekanalabschnittFeeding channel section
3939
Kerncore

Claims (7)

  1. Component of a gas turbine with a plate-shaped projecting component portion, comprising
    • a surface (2) acted upon by hot gas,
    • at least one plenum (10; 30) which is assigned solely to the component portion (1), is arranged directly adjacently to the surface (2) acted upon by hot gas and which a cooling medium can flow through convectively,
    characterized in that
    • the plenum (10; 30) issues in the form of at least one first cooling bore at the axial downstream end of the component portion,
    • second cooling bores (12) emanate from the plenum (10; 30) and the cooling bores (12) have blow-out orifices (13) which issue, upstream of the axial downstream end of the component portion (1), on the surface (2) acted upon by hot gas, with the result that a cooling film can be generated.
  2. Component according to Claim 1, characterized in that the plenum (30, 50) passes essentially completely through the component portion (1).
  3. Component according to Claim 1 or 2, characterized in that the plenum (30, 50) is formed by the casting method.
  4. Component according to Claim 3, characterized in that the plenum (30; 50) is formed by means of a multipart core (38; 39).
  5. Component according to Claim 1 or 2, characterized in that the plenum (10) and/or the blow-out orifices (12) is/are produced by the EDM method.
  6. Component according to one of the preceding claims, characterized in that the plenum (10; 30) is connected to a main plenum (5) via feed ducts (6).
  7. Component according to one of the preceding claims, characterized in that the component portion is designed in the form of an overhang (1) formed on a turbine blade (4).
EP01108008A 2000-03-31 2001-03-29 Gas turbine component Expired - Lifetime EP1138878B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10016081A DE10016081A1 (en) 2000-03-31 2000-03-31 Plate-shaped, projecting component section of a gas turbine
DE10016081 2000-03-31

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EP1138878A2 EP1138878A2 (en) 2001-10-04
EP1138878A3 EP1138878A3 (en) 2003-10-01
EP1138878B1 true EP1138878B1 (en) 2008-05-14

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US10189100B2 (en) 2008-07-29 2019-01-29 Pratt & Whitney Canada Corp. Method for wire electro-discharge machining a part
CH700320A1 (en) 2009-01-30 2010-07-30 Alstom Technology Ltd Method for producing a component of a gas turbine.
US8925201B2 (en) * 2009-06-29 2015-01-06 Pratt & Whitney Canada Corp. Method and apparatus for providing rotor discs
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US11118474B2 (en) * 2017-10-09 2021-09-14 Raytheon Technologies Corporation Vane cooling structures

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Also Published As

Publication number Publication date
US20010036407A1 (en) 2001-11-01
US6565317B2 (en) 2003-05-20
EP1138878A2 (en) 2001-10-04
DE10016081A1 (en) 2001-10-04
DE50113955D1 (en) 2008-06-26
EP1138878A3 (en) 2003-10-01

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