EP2100680B1 - Procédé destiné à la fabrication d'un composant - Google Patents

Procédé destiné à la fabrication d'un composant 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
Authority
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
Other languages
German (de)
English (en)
Other versions
EP2100680A1 (fr
Inventor
Jochen Dr. Barnikel
Jörg Dr. Schürhoff
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 EP20080003816 priority Critical patent/EP2100680B1/fr
Publication of EP2100680A1 publication Critical patent/EP2100680A1/fr
Application granted granted Critical
Publication of EP2100680B1 publication Critical patent/EP2100680B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Claims (3)

  1. Procédé de fabrication d'un élément ( 6 ) constitutif d'une turbine à vapeur,
    comprenant les stades :
    - préparation d'une couche de protection constituée en support ( 1 ),
    - le support ( 1 ) étant en un matériau céramique,
    - dépôt d'une couche ( 4 ) calorifuge sur le support ( 1 ),
    - coulée du support ( 1 ) et de la couche ( 4 ) calorifuge dans un composant ( 7 ) de coulée.
  2. Procédé suivant la revendication 1,
    dans lequel on dépose, avant la coulée du support ( 1 ) et de la couche ( 4 ) calorifuge, une couche ( 5 ) d'adhérence sur la couche ( 4 ) calorifuge.
  3. Procédé suivant la revendication 1 ou 2,
    dans lequel on dépose une couche ( 8 ) de liaison avant le dépôt de la couche ( 4 ) calorifuge.
EP20080003816 2008-02-29 2008-02-29 Procédé destiné à la fabrication d'un composant Not-in-force EP2100680B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20080003816 EP2100680B1 (fr) 2008-02-29 2008-02-29 Procédé destiné à la fabrication d'un composant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20080003816 EP2100680B1 (fr) 2008-02-29 2008-02-29 Procédé destiné à la fabrication d'un composant

Publications (2)

Publication Number Publication Date
EP2100680A1 EP2100680A1 (fr) 2009-09-16
EP2100680B1 true EP2100680B1 (fr) 2013-02-27

Family

ID=39584919

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20080003816 Not-in-force EP2100680B1 (fr) 2008-02-29 2008-02-29 Procédé destiné à la fabrication d'un composant

Country Status (1)

Country Link
EP (1) EP2100680B1 (fr)

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
DE59801547D1 (de) 1997-11-03 2001-10-25 Siemens Ag Erzeugnis, insbesondere bauteil einer gasturbine, mit keramischer wärmedämmschicht
DE10315382A1 (de) * 2003-04-04 2004-10-28 Daimlerchrysler Ag Umgusskörper zum Eingießen in ein Gussteil als Leichtmetall, Verbundgussteil daraus und Verfahren zur Herstellung des Umgusskörpers sowie Verfahren zur Herstellung des Verbundgussteiles
EP1481747A3 (fr) * 2003-05-27 2007-05-02 Alstom Technology Ltd Procédé de fabrication d'une pièce chargée par chaleur et piéce
EP1702698A1 (fr) * 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Procédé de préparation d'un composant d'une turbine
EP1734145A1 (fr) 2005-06-13 2006-12-20 Siemens Aktiengesellschaft Composant ayant un revêtement avec une barrière thermique et une couche resistante à l'erosion, procéde de manufacture et méthode pour son utilisation

Also Published As

Publication number Publication date
EP2100680A1 (fr) 2009-09-16

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