WO2008154940A1 - Procédé de réparation d'une zone d'une couche d'isolation thermique - Google Patents

Procédé de réparation d'une zone d'une couche d'isolation thermique Download PDF

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Publication number
WO2008154940A1
WO2008154940A1 PCT/EP2007/005392 EP2007005392W WO2008154940A1 WO 2008154940 A1 WO2008154940 A1 WO 2008154940A1 EP 2007005392 W EP2007005392 W EP 2007005392W WO 2008154940 A1 WO2008154940 A1 WO 2008154940A1
Authority
WO
WIPO (PCT)
Prior art keywords
mcraly
component
repair area
film
barrier coating
Prior art date
Application number
PCT/EP2007/005392
Other languages
German (de)
English (en)
Inventor
Uwe Paul
Werner Stamm
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/EP2007/005392 priority Critical patent/WO2008154940A1/fr
Priority to PCT/EP2008/054601 priority patent/WO2008155147A1/fr
Publication of WO2008154940A1 publication Critical patent/WO2008154940A1/fr

Links

Classifications

    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
    • 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
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX 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
    • 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

Definitions

  • the invention relates to a method for repairing a region of a thermal barrier coating on a component that consists of an MCrAlY film deposited on the component.
  • Thermal insulation layers for turbine blades made of nickel or cobalt superalloys in many cases comprise an MCrAlY adhesion promoter layer applied directly to the component surface and a ceramic layer lying thereon.
  • the thermal barrier coating on the turbine blade can be damaged in some areas due to wear or impact of an object. In this case, it is essential to immediately repair the damaged area of the thermal barrier coating, otherwise the turbine blade will not be sufficiently protected from heat. It can then be damaged in its structure, ultimately leading to complete component failure.
  • thermal barrier coating In order to repair the thermal barrier coating in the damaged area, according to a method generally known in the art, first the thermal barrier coating is completely removed, i. Both the ceramic layer and the underlying MCrAlY adhesion promoter layer are removed. Subsequently, in the repair area, first a new MCrAlY adhesion promoter layer on the
  • junction between the old and the new ceramic is therefore weakened, which can lead to an undefined overall performance of the repaired thermal barrier coating and in the worst case to the spalling of the thermal barrier coating in the repair area.
  • This object is achieved according to the invention in that the shape and size of the repair area is determined after the removal of the thermal barrier coating, an MCrAlY film is produced having the shape and size of the repair area, the MCrAlY film is placed completely over the repair area on the component, the MCrAlY film is applied. Heat-treated film for connection to the component and the side of the MCrAlY film facing away from the component is coated with a ceramic.
  • the basic idea of the invention is therefore to determine the repair area in terms of shape and size after the thermal barrier coating has been removed therefrom. Subsequently, an MCrAlY film is produced which has the shape and size of the repair area. Then the MCrAlY film is placed on the component in such a way that it Repair area completely covered. In order to effect a connection of the MCrAlY film to the component, it is subjected to a heat treatment. Finally, the side of the MCrAlY film facing away from the component is coated with a ceramic.
  • the shape and size of the repair area is determined by means of optical methods.
  • optical methods especially photographic and in particular 3-D photographic methods are suitable.
  • the required data regarding shape and size of the repair area can be determined easily, quickly and with high accuracy.
  • MCrAlY films are commercially available in a wide variety of strengths. These can be quickly and with the highest precision cut to the required size with the aid of a laser.
  • the MCrAlY film is subjected to a heat treatment, in particular in a vacuum oven, for connection to the component.
  • the MCrAlY film can also be locally subjected to a heat treatment by induction.
  • the ceramic can be sprayed onto the side of the MCrAlY foil facing away from the component.
  • APS atmospheric plasma spraying
  • a development of the invention provides that the thermal barrier coating in the repair area is removed mechanically, for example by abrading, chemically or electrochemically.
  • the single figure shows a schematic representation of a turbine blade 1 with a blade platform 2 and an associated blade 3.
  • the turbine blade 1 is provided on the surface with a thermal barrier coating 4, the latter consisting of an MCrAlY adhesion promoter layer applied directly to the turbine blade 1 and a ceramic layer lying thereon.
  • the thermal barrier coating 4 is damaged on the blade platform 2 in a repair area 5.
  • the thermal barrier coating 4 in the repair area 5 is completely removed, for example by abrading. Both the ceramic layer and the MCrAlY adhesion promoter layer are removed in the repair area 5.
  • the shape and size of the repair area 5 is determined exactly. This can be done, for example, optically with the aid of a digital camera and a connected data processing system for the evaluation of the received camera data.
  • an MCrAlY film 6 is then produced, which determines the exact shape and size of the Repair area 5 has.
  • a freestanding MCrAlY film which has the same thickness as the MCrAlY Haftverraittler Anlagen be cut using a laser.
  • the MCrAlY film 6 is then placed on the blade platform 2 so that it completely covers the repair area 5. It is subjected to a heat treatment in order to bond it to the surface of the blade platform 2.
  • the entire turbine blade 1 can be heated with the MCrAlY film 6 in a vacuum oven.
  • the blade platform 2 facing away from the MCrAlY film 6 is coated with a ceramic.
  • a ceramic which is identical to the ceramic of the ceramic layer 6 is applied to the MCrAlY foil 6, for example by atmospheric plasma spraying.
  • a portion of the newly applied ceramic layer can then be ground away, so that it is planar to the ceramic layer.
  • a particular advantage of the method according to the invention is that the new MCrAlY layer can be applied in the repair area 5 without the risk of the ceramic layer being contaminated.

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)
  • General Engineering & Computer Science (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé de réparation d'une zone d'une couche d'isolation thermique (4) sur un composant (1), couche qui se compose d'une couche d'accrochage en MCrAlY apposée sur le composant (1) et d'une couche de matériau céramique disposée sur la couche d'accrochage. Selon ce procédé : on élimine la couche d'isolation thermique (4) dans la zone à réparer (5) ; on détermine la forme et la taille de la zone à réparer (5) suite à l'élimination de la couche d'isolation thermique ; on fabrique une feuille de MCrAlY (6) ayant la forme et la taille de la zone à réparer ; on place la feuille de MCrAlY (6) sur le composant (1) en recouvrant entièrement la zone à réparer (5) ; on soumet la feuille de MCrAlY (6) à un traitement thermique pour la lier au composant (1) ; et on revêt d'un matériau céramique le côté de la feuille de MCrAlY (6) qui est opposé au composant.
PCT/EP2007/005392 2007-06-19 2007-06-19 Procédé de réparation d'une zone d'une couche d'isolation thermique WO2008154940A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/EP2007/005392 WO2008154940A1 (fr) 2007-06-19 2007-06-19 Procédé de réparation d'une zone d'une couche d'isolation thermique
PCT/EP2008/054601 WO2008155147A1 (fr) 2007-06-19 2008-04-16 Procédé de réparation d'une zone d'une couche d'isolation thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2007/005392 WO2008154940A1 (fr) 2007-06-19 2007-06-19 Procédé de réparation d'une zone d'une couche d'isolation thermique

Publications (1)

Publication Number Publication Date
WO2008154940A1 true WO2008154940A1 (fr) 2008-12-24

Family

ID=38691837

Family Applications (2)

Application Number Title Priority Date Filing Date
PCT/EP2007/005392 WO2008154940A1 (fr) 2007-06-19 2007-06-19 Procédé de réparation d'une zone d'une couche d'isolation thermique
PCT/EP2008/054601 WO2008155147A1 (fr) 2007-06-19 2008-04-16 Procédé de réparation d'une zone d'une couche d'isolation thermique

Family Applications After (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/054601 WO2008155147A1 (fr) 2007-06-19 2008-04-16 Procédé de réparation d'une zone d'une couche d'isolation thermique

Country Status (1)

Country Link
WO (2) WO2008154940A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015200513A1 (de) * 2015-01-15 2016-07-21 Siemens Aktiengesellschaft Lokale Schadenserfassung und lokale Wärmebehandlungund Vorrichtung dafür
DE102019217580A1 (de) * 2019-11-14 2021-05-20 Siemens Aktiengesellschaft Reparatur von beschichteten Bauteilen mittels Designanpassung

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1065297A2 (fr) * 1999-06-29 2001-01-03 General Electric Company Procédé pour fabriquer des revêtements résistants à l'usure et articles ainsi revêtus
EP1091020A1 (fr) * 1999-10-04 2001-04-11 General Electric Company Procédé d'application d'un revêtement de liaison et une couche de barrière thermique sur un substrat métallique et articles ainsi revêtus
US20020128790A1 (en) * 2001-03-09 2002-09-12 Donald Woodmansee System and method of automated part evaluation including inspection, disposition recommendation and refurbishment process determination
EP1256635A1 (fr) * 2001-05-08 2002-11-13 General Electric Company Procédé pour appliquer des revêtements d'aluminium à diffuser sur des régions sélectives d'un composant de moteur à turbine
EP1312438A1 (fr) * 2001-11-19 2003-05-21 Mitsubishi Heavy Industries, Ltd. Procédé pour réparer automatiquement les fissures et dispositif utilisé dans un tel procédé
WO2003097293A1 (fr) * 2002-05-14 2003-11-27 C.A. Patents, L.L.C. Procede de formation de preformes metalliques par la metallisation
EP1507236A1 (fr) * 2003-08-15 2005-02-16 Siemens Westinghouse Power Corporation Système et méthode de traitement de données d'inspection pour l'évaluation de la dégradation du revêtement de composants.
US20050235493A1 (en) * 2004-04-22 2005-10-27 Siemens Westinghouse Power Corporation In-frame repair of gas turbine components
DE102004026352A1 (de) * 2004-05-26 2005-12-15 Alstom Technology Ltd Verfahren zum Instandsetzen einer Beschichtung
DE102004028672A1 (de) * 2004-06-12 2006-01-05 Mtu Aero Engines Gmbh Verfahren zum Beschichten von Innenflächen hohler Gasturbinenschaufeln

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1065297A2 (fr) * 1999-06-29 2001-01-03 General Electric Company Procédé pour fabriquer des revêtements résistants à l'usure et articles ainsi revêtus
EP1091020A1 (fr) * 1999-10-04 2001-04-11 General Electric Company Procédé d'application d'un revêtement de liaison et une couche de barrière thermique sur un substrat métallique et articles ainsi revêtus
US20020128790A1 (en) * 2001-03-09 2002-09-12 Donald Woodmansee System and method of automated part evaluation including inspection, disposition recommendation and refurbishment process determination
EP1256635A1 (fr) * 2001-05-08 2002-11-13 General Electric Company Procédé pour appliquer des revêtements d'aluminium à diffuser sur des régions sélectives d'un composant de moteur à turbine
EP1312438A1 (fr) * 2001-11-19 2003-05-21 Mitsubishi Heavy Industries, Ltd. Procédé pour réparer automatiquement les fissures et dispositif utilisé dans un tel procédé
WO2003097293A1 (fr) * 2002-05-14 2003-11-27 C.A. Patents, L.L.C. Procede de formation de preformes metalliques par la metallisation
EP1507236A1 (fr) * 2003-08-15 2005-02-16 Siemens Westinghouse Power Corporation Système et méthode de traitement de données d'inspection pour l'évaluation de la dégradation du revêtement de composants.
US20050235493A1 (en) * 2004-04-22 2005-10-27 Siemens Westinghouse Power Corporation In-frame repair of gas turbine components
DE102004026352A1 (de) * 2004-05-26 2005-12-15 Alstom Technology Ltd Verfahren zum Instandsetzen einer Beschichtung
DE102004028672A1 (de) * 2004-06-12 2006-01-05 Mtu Aero Engines Gmbh Verfahren zum Beschichten von Innenflächen hohler Gasturbinenschaufeln

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015200513A1 (de) * 2015-01-15 2016-07-21 Siemens Aktiengesellschaft Lokale Schadenserfassung und lokale Wärmebehandlungund Vorrichtung dafür
DE102019217580A1 (de) * 2019-11-14 2021-05-20 Siemens Aktiengesellschaft Reparatur von beschichteten Bauteilen mittels Designanpassung
US11724343B2 (en) 2019-11-14 2023-08-15 Siemens Energy Global GmbH & Co. KG Repair of coated components using design adaptation

Also Published As

Publication number Publication date
WO2008155147A1 (fr) 2008-12-24

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