EP2100680B1 - Method for producing a component - Google Patents

Method for producing a component Download PDF

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Publication number
EP2100680B1
EP2100680B1 EP20080003816 EP08003816A EP2100680B1 EP 2100680 B1 EP2100680 B1 EP 2100680B1 EP 20080003816 EP20080003816 EP 20080003816 EP 08003816 A EP08003816 A EP 08003816A EP 2100680 B1 EP2100680 B1 EP 2100680B1
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EP
European Patent Office
Prior art keywords
carrier
thermal barrier
barrier coating
component
layer
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.)
Not-in-force
Application number
EP20080003816
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German (de)
French (fr)
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EP2100680A1 (en
Inventor
Jochen Dr. Barnikel
Jörg Dr. Schürhoff
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Siemens AG
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Siemens AG
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Publication date
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Priority to EP20080003816 priority Critical patent/EP2100680B1/en
Publication of EP2100680A1 publication Critical patent/EP2100680A1/en
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Publication of EP2100680B1 publication Critical patent/EP2100680B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/08—Casting in, on, or around objects which form part of the product for building-up linings or coverings, e.g. of anti-frictional metal
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C6/00—Coating by casting molten material on the substrate

Definitions

  • the invention relates to a method for producing a component, in particular a steam turbine component.
  • the invention further relates to a layer system for a component, in particular for a steam turbine, comprising a protective layer, a heat-insulating layer applied to the protective layer, an adhesive layer applied to the thermal-barrier layer and a cast component cast with the adhesive layer.
  • Thermal barrier coatings applied to components are known in the gas turbine industry. In the EP 1 029 115 For example, such a thermal barrier coating is described.
  • thermal barrier coatings it is possible to use components of turbomachines, such as steam turbines, at higher temperatures. Without a thermal barrier coating, the use of a component would only be possible up to a temperature that depends on the base material of the component.
  • Thermally stressed areas are formed with such thermal barrier coatings, wherein these components by known coating methods such as atmospheric plasma spraying (APS), vacuum plasma spraying (VPS), low-pressure plasma spraying (LPPS) and by chemical or physical coating methods (CVD, PVD) are coated.
  • APS atmospheric plasma spraying
  • VPS vacuum plasma spraying
  • LPPS low-pressure plasma spraying
  • CVD chemical or physical coating methods
  • thermal barrier coating on the steam turbine component by means of the known coating methods is complicated. It would be desirable to be able to produce a steam turbine component inexpensively and quickly with a thermal barrier coating.
  • the invention begins, whose object is to provide a method for producing a component, which can be produced quickly and easily.
  • the invention thus completely avoids the idea of coating the thermal barrier coating on the steam turbine component by means of one of the known coating methods. Rather, the invention is based on the idea of initially applying the thermal barrier coating on a carrier.
  • This carrier has both mechanical and chemical properties, which result in that the carrier can be used in thermally loaded areas of a steam turbine.
  • the thermal barrier coating is applied to the substrate by means of one of the known coating methods.
  • the carrier is poured with the thermal barrier coating in a cast component. After solidification of the casting material, the steam turbine component is completed, wherein the thermal barrier coating has a connection to the casting component.
  • the carrier remains in this case and is not removed as in other known casting methods, such as leaching by or mechanical removal.
  • the carrier thus fulfills essentially two functions.
  • the carrier forms a receptacle for a thermal barrier coating which is to be applied to a cast component.
  • the carrier forms a protective layer, which protects the thermal barrier coating against, for example, erosion.
  • the carrier can also serve as oxidation protection.
  • thermal barrier coating or an adhesive layer and further layers are known from WO 2006/133980 A1 disclosed.
  • the content of WO 2006/133980 A1 is thus fully included in the disclosure of this application.
  • an adhesive layer is applied to the thermal barrier coating prior to casting of the carrier and the thermal barrier coating.
  • the adhesive layer has the task of allowing a good connection between the thermal barrier coating and the casting component.
  • An example of an adhesive layer can turn from the WO 2006/133980 A1 be removed.
  • a bonding layer is applied to the carrier before the application of the thermal barrier coating.
  • the connection layer has the task of enabling a good connection between the thermal barrier coating and the carrier.
  • a corresponding layer of the WO 2006/133980 A1 be removed.
  • the FIG. 1 shows a cross-sectional view of the carrier 1.
  • the carrier 1 may be made of a heat-resistant material.
  • the carrier 1 has a geometric shape which is suitable for being able to be arranged in a turbomachine at locations that are thermally stressed.
  • Thermally stressed points in a turbomachine such as in a steam turbine, are, for example, steam-exposed surfaces.
  • the inflow region of a steam turbine would be, for example, a vapor-exposed region which is thermally stressed.
  • Ceramic materials can be used:
  • the carrier 1 has an inside surface 2.
  • the inside surface 2 is the surface facing the vapor after the completion of the carrier 1. This means that the inside surface 2 is exposed to a comparatively high temperature steam.
  • the carrier 1 has an outside surface 3.
  • a bonding layer 8 is applied on this outside surface 3.
  • the connecting layer 8 consists of a suitable material. Examples of a suitable material are in the WO 2006/133980 A1 disclosed.
  • the bonding layer 8 can be applied to the substrate 1 by means of known coating methods.
  • a thermal barrier coating 4 is applied to the bonding layer 8. With the bonding layer 8, the thermal barrier coating 4 can be optimally connected to the carrier.
  • the FIG. 2 discloses a cross-sectional view of a portion of a completed steam turbine component 6.
  • the carrier 1 coated with the thermal barrier coating 4 is poured into a cast component 7.
  • the casting component 7 has a metallic character.
  • An example of a material selection for the casting component 7 is shown in FIG WO 2006/133980 A1 disclosed.
  • the cast component 7 could be, for example, a 1% to 2% chromium steel, a cast iron or a nickel-based alloy.
  • the carrier 1 After the casting process, the carrier 1 remains in the casting component 7, whereby a complete steam turbine component 6 is formed.
  • the carrier 1 protects the thermal barrier coating 4 from erosion. As a result, for example, penetration of the vapor into the thermal barrier coating 4 is effectively avoided.
  • Another function of the carrier 1 is provided by the mechanical protection of the casting component 7 during assembly, during transport or during a revision.
  • a significant advantage of the invention is that the carrier 1 can easily assume complicated geometries of an inner contour, as they occur in steam turbines.
  • the coating of the carrier 1 with the thermal barrier coating 4 leads to a simplification of the overall production of the steam turbine component 6.
  • the production method according to the invention offers the advantage that an erosion protection layer can be saved as a third coating layer, since the carrier 1 fulfills the function of an erosion protection layer. Even with damage e.g. By disrupting a loss of the thermal barrier coating 4 by using a carrier 1 is effectively avoided.
  • Another significant advantage is that even thermal barrier coatings 4 can be used with poor adhesion to the casting component 7, because the adhesion of the thermal barrier coating 4 to the carrier 1 is the crucial component in the manufacturing process.
  • a bonding layer is applied to the carrier 1 prior to the application of the thermal barrier coating 4 on the carrier 1.
  • This connection layer is in the FIG. 1 and in the FIG. 2 not shown in detail.
  • the connection layer has the task of enabling an optimal connection between the thermal barrier coating 4 and the carrier 1.
  • FIG. 3 shows a section of a finished steam turbine component 6.
  • the difference from the in Fig. 2 shown steam turbine component 6 is that between the thermal barrier coating 4 and the carrier 1, the optionally arranged compound layer 8 is shown.

Description

Die Erfindung betrifft ein Verfahren zum Herstellen eines Bauteils, insbesondere eines Dampfturbinenbauteils. Des Weiteren betrifft die Erfindung ein Schichtsystem für ein Bauteil, insbesondere für eine Dampfturbine, umfassend eine Schutzschicht, eine auf der Schutzschicht aufgebrachte Wärmedämmschicht, eine auf der Wärmedämmschicht aufgebrachte Haftschicht und einer mit der Haftschicht vergossenen Gusskomponente.The invention relates to a method for producing a component, in particular a steam turbine component. The invention further relates to a layer system for a component, in particular for a steam turbine, comprising a protective layer, a heat-insulating layer applied to the protective layer, an adhesive layer applied to the thermal-barrier layer and a cast component cast with the adhesive layer.

Wärmedämmschichten, die auf Bauteilen aufgebracht werden, sind aus dem Gasturbinenbau bekannt. In der EP 1 029 115 ist beispielsweise eine derartige Wärmedämmschicht beschrieben.Thermal barrier coatings applied to components are known in the gas turbine industry. In the EP 1 029 115 For example, such a thermal barrier coating is described.

Mit Hilfe von Wärmedämmschichten ist es möglich, Bauteile von Strömungsmaschinen, wie beispielsweise Dampfturbinen, bei höheren Temperaturen einsetzen zu können. Ohne eine Wärmedämmschicht wäre der Einsatz eines Bauteils nur bis zu einer Temperatur möglich, die vom Grundwerkstoff des Bauteils abhängig ist.With the help of thermal barrier coatings, it is possible to use components of turbomachines, such as steam turbines, at higher temperatures. Without a thermal barrier coating, the use of a component would only be possible up to a temperature that depends on the base material of the component.

Thermisch besonders belastete Bereiche werden mit derartigen Wärmedämmschichten ausgebildet, wobei diese Komponenten mittels bekannter Beschichtungsverfahren wie atmosphärisches Plasmaspritzen (APS), Vakuumplasmaspritzen (VPS), Niedrigdruckplasmaspritzen (LPPS) sowie durch chemische oder physikalische Beschichtungsmethoden (CVD, PVD) beschichtet werden.Thermally stressed areas are formed with such thermal barrier coatings, wherein these components by known coating methods such as atmospheric plasma spraying (APS), vacuum plasma spraying (VPS), low-pressure plasma spraying (LPPS) and by chemical or physical coating methods (CVD, PVD) are coated.

Das Aufbringen der Wärmedämmschicht auf das Dampfturbinenbauteil mittels der bekannten Beschichtungsverfahren ist aufwändig. Wünschenswert wäre es, ein Dampfturbinenbauteil kostengünstig und schnell mit einer Wärmedämmschicht herstellen zu können.The application of the thermal barrier coating on the steam turbine component by means of the known coating methods is complicated. It would be desirable to be able to produce a steam turbine component inexpensively and quickly with a thermal barrier coating.

An dieser Stelle setzt die Erfindung an, dessen Aufgabe es ist, ein Verfahren zum Herstellen eines Bauteils anzugeben, das schnell und einfach hergestellt werden kann.At this point, the invention begins, whose object is to provide a method for producing a component, which can be produced quickly and easily.

Die auf das Verfahren hin gerichtete Aufgabe wird durch ein Verfahren zum Herstellen eines Bauteils, insbesondere eines Dampfturbinenbauteils, mit den Schritten:

  • Bereitstellen einer als Träger ausgebildeten Schutzschicht
  • Aufbringen einer Wärmedämmschicht auf den Träger
  • Eingießen des Trägers und der Wärmedämmschicht in eine Gusskomponente
gelöst.The task directed towards the method is achieved by a method for producing a component, in particular a steam turbine component, with the steps:
  • Providing a protective layer formed as a carrier
  • Applying a thermal barrier coating on the carrier
  • Pouring the carrier and the thermal barrier coating into a cast component
solved.

Die Erfindung geht somit völlig weg von dem Gedanken, die Wärmedämmschicht auf das Dampfturbinenbauteil mittels einer der bekannten Beschichtungsverfahren zu beschichten. Vielmehr geht die Erfindung von dem Gedanken aus, die Wärmedämmschicht zunächst auf einen Träger aufzubringen. Dieser Träger weist sowohl mechanische als auch chemische Eigenschaften auf, die dazu führen, dass der Träger in thermisch belasteten Bereichen einer Dampfturbine eingesetzt werden kann. Die Wärmedämmschicht wird mittels einer der bekannten Beschichtungsverfahren auf den Träger aufgebracht. Anschließend wird der Träger mit der Wärmedämmschicht in eine Gusskomponente eingegossen. Nach Erstarren des Gießmaterials ist das Dampfturbinenbauteil fertig gestellt, wobei die Wärmedämmschicht eine Verbindung zu der Gusskomponente aufweist. Der Träger bleibt hierbei bestehen und wird nicht wie in anderen bekannten Gießverfahren entfernt, wie z.B. durch Auslaugen durch oder mechanische Entfernung. Der Träger erfüllt somit im Wesentlichen zwei Funktionen. Zum einen bildet der Träger eine Aufnahmemöglichkeit für eine Wärmedämmschicht, die auf einer Gusskomponente aufzutragen ist. Zum anderen bildet der Träger nach Fertigstellung des Dampfturbinenbauteils eine Schutzschicht, die die Wärmedämmschicht vor beispielsweise Erosionen schützt. Der Träger kann ebenso als Oxidationsschutz dienen.The invention thus completely avoids the idea of coating the thermal barrier coating on the steam turbine component by means of one of the known coating methods. Rather, the invention is based on the idea of initially applying the thermal barrier coating on a carrier. This carrier has both mechanical and chemical properties, which result in that the carrier can be used in thermally loaded areas of a steam turbine. The thermal barrier coating is applied to the substrate by means of one of the known coating methods. Subsequently, the carrier is poured with the thermal barrier coating in a cast component. After solidification of the casting material, the steam turbine component is completed, wherein the thermal barrier coating has a connection to the casting component. The carrier remains in this case and is not removed as in other known casting methods, such as leaching by or mechanical removal. The carrier thus fulfills essentially two functions. On the one hand, the carrier forms a receptacle for a thermal barrier coating which is to be applied to a cast component. On the other hand, after completion of the steam turbine component, the carrier forms a protective layer, which protects the thermal barrier coating against, for example, erosion. The carrier can also serve as oxidation protection.

Beispiele für eine Wärmedämmschicht bzw. einer Haftschicht und weitere Schichten sind aus der WO 2006/133980 A1 offenbart. Der Inhalt der WO 2006/133980 A1 wird somit vollumfänglich mit in den Offenbarungsgehalt dieser Anmeldung aufgenommen.Examples of a thermal barrier coating or an adhesive layer and further layers are known from WO 2006/133980 A1 disclosed. The content of WO 2006/133980 A1 is thus fully included in the disclosure of this application.

Vorteilhafterweise wird vor dem Gießen des Trägers und der Wärmedämmschicht eine Haftschicht auf die Wärmedämmschicht aufgebracht. Die Haftschicht hat die Aufgabe, eine gute Verbindung zwischen der Wärmedämmschicht und der Gusskomponente zu ermöglichen. Ein Beispiel für eine Haftschicht kann wiederum aus der WO 2006/133980 A1 entnommen werden.Advantageously, an adhesive layer is applied to the thermal barrier coating prior to casting of the carrier and the thermal barrier coating. The adhesive layer has the task of allowing a good connection between the thermal barrier coating and the casting component. An example of an adhesive layer can turn from the WO 2006/133980 A1 be removed.

In einer weiteren vorteilhaften Weiterbildung des Verfahrens wird vor dem Aufbringen der Wärmedämmschicht eine Verbindungsschicht auf den Träger aufgebracht. Die Verbindungsschicht hat die Aufgabe, eine gute Verbindung zwischen der Wärmedämmschicht und den Träger zu ermöglichen. Als Beispiele für eine Zusammensetzung der Verbindungsschicht kann eine entsprechende Schicht aus der WO 2006/133980 A1 entnommen werden.In a further advantageous embodiment of the method, a bonding layer is applied to the carrier before the application of the thermal barrier coating. The connection layer has the task of enabling a good connection between the thermal barrier coating and the carrier. As examples of a compound layer composition, a corresponding layer of the WO 2006/133980 A1 be removed.

Ausführungsbeispiele der Erfindung werden nachfolgend anhand der Zeichnungen beschrieben. Diese sollen das Ausführungsbeispiel nicht maßstäblich darstellen, vielmehr sind die Zeichnungen, wozu Erläuterungen dienen, in schematischer und/oder leicht versetzter Form ausgeführt. Im Hinblick auf Ergänzungen der aus der Zeichnung unmittelbar erkennbaren Lehren wird auf den einschlägigen Stand der Technik verwiesen.Embodiments of the invention will be described below with reference to the drawings. These are not intended to represent the embodiment to scale, but the drawings, to which explanations serve, executed in a schematic and / or slightly offset form. With regard to additions to the teachings directly recognizable from the drawing reference is made to the relevant prior art.

Es zeigen:

Figur 1
eine Schnittansicht des Trägers mit der Wärmedämmschicht,
Figur 2
ein nach dem Gießen fertig gestelltes Dampfturbinenbauteil,
Figur 3
ein Ausschnitt eines nach dem Gießen fertig gestellten Dampfturbinenbauteils mit einer Verbindungsschicht.
Show it:
FIG. 1
a sectional view of the carrier with the thermal barrier coating,
FIG. 2
a finished after casting steam turbine component,
FIG. 3
a section of a finished after casting steam turbine component with a connecting layer.

Komponenten mit ähnlicher Wirkungsweise weisen dieselben Bezugszeichen auf.Components with similar operation have the same reference numerals.

Die Figur 1 zeigt eine Querschnittsansicht des Trägers 1. Der Träger 1 kann aus einem wärmebeständigen Material sein. Des Weiteren weist der Träger 1 eine geometrische Form auf, die dazu geeignet ist, um in einer Strömungsmaschine an Stellen angeordnet werden zu können, die thermisch belastet sind. Thermisch belastete Stellen in einer Strömungsmaschine, wie z.B. in einer Dampfturbine, sind beispielsweise dampfbeaufschlagte Oberflächen. Der Einströmungsbereich einer Dampfturbine wäre beispielsweise ein dampfbeaufschlagter Bereich, der thermisch belastet wird.The FIG. 1 shows a cross-sectional view of the carrier 1. The carrier 1 may be made of a heat-resistant material. Furthermore, the carrier 1 has a geometric shape which is suitable for being able to be arranged in a turbomachine at locations that are thermally stressed. Thermally stressed points in a turbomachine, such as in a steam turbine, are, for example, steam-exposed surfaces. The inflow region of a steam turbine would be, for example, a vapor-exposed region which is thermally stressed.

Als Trägermaterialien können keramische Materialien verwendet werden:As support materials ceramic materials can be used:

Der Träger 1 weist eine innenseitige Fläche 2 auf. Die innenseitige Fläche 2 ist die Fläche, die nach der Fertigstellung des Trägers 1 dem Dampf zugewandt ist. Das bedeutet, dass die innenseitige Fläche 2 mit einem Dampf mit vergleichsweise hoher Temperatur beaufschlagt wird. Des Weiteren weist der Träger 1 eine außenseitige Fläche 3 auf. Auf diese außenseitige Fläche 3 wird eine Verbindungsschicht 8 aufgebracht. Die Verbindungsschicht 8 besteht hierbei aus einem geeigneten Material. Beispiele für ein geeignetes Material sind in der WO 2006/133980 A1 offenbart. Die Verbindungsschicht 8 kann mittels bekannter Beschichtungsverfahren auf den Träger 1 aufgebracht werden.The carrier 1 has an inside surface 2. The inside surface 2 is the surface facing the vapor after the completion of the carrier 1. This means that the inside surface 2 is exposed to a comparatively high temperature steam. Furthermore, the carrier 1 has an outside surface 3. On this outside surface 3, a bonding layer 8 is applied. The connecting layer 8 consists of a suitable material. Examples of a suitable material are in the WO 2006/133980 A1 disclosed. The bonding layer 8 can be applied to the substrate 1 by means of known coating methods.

In einem weiteren Herstellungsverfahrenschritt wird eine Wärmedämmschicht 4 auf die Verbindungsschicht 8 aufgetragen. Mit der Verbindungsschicht 8 kann die Wärmedämmschicht 4 optimal an den Träger angebunden werden.In a further manufacturing process step, a thermal barrier coating 4 is applied to the bonding layer 8. With the bonding layer 8, the thermal barrier coating 4 can be optimally connected to the carrier.

Die Figur 2 offenbart eine Querschnittsansicht eines Teils eines fertig gestellten Dampfturbinenbauteils 6. Der mit der Wärmedämmschicht 4 beschichtete Träger 1 wird in eine Gusskomponente 7 eingegossen. Die Gusskomponente 7 weist metallischen Charakter auf. Ein Beispiel für eine Materialauswahl für die Gusskomponente 7 ist in der WO 2006/133980 A1 offenbart. Die Gusskomponente 7 könnte beispielsweise ein 1% - 2%iger Chromstahl sein, eines Gusseisens oder aus einer Nickelbasis-Legierung bestehen.The FIG. 2 discloses a cross-sectional view of a portion of a completed steam turbine component 6. The carrier 1 coated with the thermal barrier coating 4 is poured into a cast component 7. The casting component 7 has a metallic character. An example of a material selection for the casting component 7 is shown in FIG WO 2006/133980 A1 disclosed. The cast component 7 could be, for example, a 1% to 2% chromium steel, a cast iron or a nickel-based alloy.

Nach dem Gießvorgang verbleibt der Träger 1 in der Gusskomponente 7, wodurch ein komplettes Dampfturbinenbauteil 6 entsteht. Der Träger 1 schützt hierbei die Wärmedämmschicht 4 vor Erosion. Dadurch ist beispielsweise ein Eindringen des Dampfes in die Wärmedämmschicht 4 wirksam vermieden.After the casting process, the carrier 1 remains in the casting component 7, whereby a complete steam turbine component 6 is formed. The carrier 1 protects the thermal barrier coating 4 from erosion. As a result, for example, penetration of the vapor into the thermal barrier coating 4 is effectively avoided.

Eine weitere Funktion des Trägers 1 ist durch den mechanischen Schutz der Gusskomponente 7 während einer Montage, während eines Transportes oder während einer Revision gegeben.Another function of the carrier 1 is provided by the mechanical protection of the casting component 7 during assembly, during transport or during a revision.

Ein wesentlicher Vorteil der Erfindung ist, dass der Träger 1 komplizierte Geometrien einer Innenkontur, wie sie bei Dampfturbinen vorkommen, leicht annehmen kann. Die Beschichtung des Trägers 1 mit der Wärmedämmschicht 4 führt zu einer Vereinfachung der Gesamtherstellung des Dampfturbinenbauteils 6.A significant advantage of the invention is that the carrier 1 can easily assume complicated geometries of an inner contour, as they occur in steam turbines. The coating of the carrier 1 with the thermal barrier coating 4 leads to a simplification of the overall production of the steam turbine component 6.

Des Weiteren bietet das erfindungsgemäße Herstellungsverfahren den Vorteil, dass eine Erosionsschutzschicht als dritte Beschichtungslage gespart werden kann, da der Träger 1 die Funktion einer Erosionsschutzschicht erfüllt. Selbst bei einer Beschädigung z.B. durch Zerrüttung ist ein Verlust der Wärmedämmschicht 4 durch das Verwenden eines Trägers 1 wirksam vermieden. Ein weiterer wesentlicher Vorteil ist, dass selbst Wärmedämmschichten 4 mit einer schlechten Haftung zur Gusskomponente 7 eingesetzt werden können, denn die Haftung der Wärmedämmschicht 4 an den Träger 1 ist die entscheidende Komponente bei dem Herstellungsverfahren.Furthermore, the production method according to the invention offers the advantage that an erosion protection layer can be saved as a third coating layer, since the carrier 1 fulfills the function of an erosion protection layer. Even with damage e.g. By disrupting a loss of the thermal barrier coating 4 by using a carrier 1 is effectively avoided. Another significant advantage is that even thermal barrier coatings 4 can be used with poor adhesion to the casting component 7, because the adhesion of the thermal barrier coating 4 to the carrier 1 is the crucial component in the manufacturing process.

Des Weiteren wird ein Abplatzen der Wärmedämmschicht 4 von der Gusskomponente 7 aufgrund von unterschiedlichen Wärmeausdehnungskoeffizienten durch die Verwendung des Trägers 1 wirksam vermieden.Furthermore, chipping of the thermal barrier coating 4 from the casting component 7 due to different thermal expansion coefficients by the use of the carrier 1 is effectively avoided.

In einer alternativen Ausführungsform wird vor dem Aufbringen der Wärmedämmschicht 4 auf den Träger 1 eine Verbindungsschicht auf den Träger 1 angebracht. Diese Verbindungsschicht ist in der Figur 1 und in der Figur 2 nicht näher dargestellt. Die Verbindungsschicht hat die Aufgabe, eine optimale Verbindung zwischen der Wärmedämmschicht 4 und dem Träger 1 zu ermöglichen.In an alternative embodiment, a bonding layer is applied to the carrier 1 prior to the application of the thermal barrier coating 4 on the carrier 1. This connection layer is in the FIG. 1 and in the FIG. 2 not shown in detail. The connection layer has the task of enabling an optimal connection between the thermal barrier coating 4 and the carrier 1.

Die Figur 3 zeigt einen Ausschnitt eines fertig gestellten Dampfturbinenbauteils 6. Der Unterschied zu dem in Fig. 2 dargestellten Dampfturbinenbauteils 6 liegt darin, dass zwischen der Wärmedämmschicht 4 und dem Träger 1 die optional angeordnete Verbindungsschicht 8 dargestellt ist.The FIG. 3 shows a section of a finished steam turbine component 6. The difference from the in Fig. 2 shown steam turbine component 6 is that between the thermal barrier coating 4 and the carrier 1, the optionally arranged compound layer 8 is shown.

Claims (3)

  1. Method for producing a steam turbine component (6), comprising the following steps:
    - providing a protective layer in the form of a carrier (1) ,
    wherein the carrier (1) is formed from a ceramic material,
    - applying a thermal barrier coating (4) to the carrier (1), and
    - casting the carrier (1) and the thermal barrier coating (4) into a cast component (7).
  2. Method according to Claim 1,
    wherein a bonding layer (5) is applied to the thermal barrier coating (4) before the carrier (1) and the thermal barrier coating (4) are cast in.
  3. Method according to Claim 1 or 2,
    wherein a connecting layer (8) is applied to the carrier (1) before the thermal barrier coating (4) is applied.
EP20080003816 2008-02-29 2008-02-29 Method for producing a component Not-in-force EP2100680B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20080003816 EP2100680B1 (en) 2008-02-29 2008-02-29 Method for producing a component

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20080003816 EP2100680B1 (en) 2008-02-29 2008-02-29 Method for producing a component

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EP2100680A1 EP2100680A1 (en) 2009-09-16
EP2100680B1 true EP2100680B1 (en) 2013-02-27

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EP20080003816 Not-in-force EP2100680B1 (en) 2008-02-29 2008-02-29 Method for producing a component

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Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8818214D0 (en) * 1988-07-30 1988-09-01 T & N Technology Ltd Pistons
EP1029115B1 (en) 1997-11-03 2001-09-19 Siemens Aktiengesellschaft Product,especially a gas turbine component, with a ceramic heat insulating layer
DE10315382A1 (en) * 2003-04-04 2004-10-28 Daimlerchrysler Ag Cast body used as a cylinder liner has a thermally sprayed adhesion promoting layer made from pure nickel arranged on the outer surface of the cast body facing the cast part
EP1481747A3 (en) * 2003-05-27 2007-05-02 Alstom Technology Ltd Method for producing a heat loaded component and component
EP1702698A1 (en) * 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Method for the production of a turbine part
EP1734145A1 (en) 2005-06-13 2006-12-20 Siemens Aktiengesellschaft Coating system for a component having a thermal barrier coating and an erosion resistant coating, method for manufacturing and method for using said component

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