EP1591549B1 - Procédé de réparation d'une dégradation locale d'un revêtement de barrière thermique d'une pièce - Google Patents

Procédé de réparation d'une dégradation locale d'un revêtement de barrière thermique d'une pièce Download PDF

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Publication number
EP1591549B1
EP1591549B1 EP04101783A EP04101783A EP1591549B1 EP 1591549 B1 EP1591549 B1 EP 1591549B1 EP 04101783 A EP04101783 A EP 04101783A EP 04101783 A EP04101783 A EP 04101783A EP 1591549 B1 EP1591549 B1 EP 1591549B1
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EP
European Patent Office
Prior art keywords
coat
thermal barrier
layer
process according
bond coat
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.)
Expired - Lifetime
Application number
EP04101783A
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German (de)
English (en)
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EP1591549A1 (fr
Inventor
Andreas Bögli
Maxim Dr. Konter
Regina Dr. Schlegel
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP04101783A priority Critical patent/EP1591549B1/fr
Priority to DE502004010936T priority patent/DE502004010936D1/de
Priority to AT04101783T priority patent/ATE462023T1/de
Publication of EP1591549A1 publication Critical patent/EP1591549A1/fr
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Publication of EP1591549B1 publication Critical patent/EP1591549B1/fr
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    • 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
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
    • 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
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00019—Repairing or maintaining combustion chamber liners or subparts

Definitions

  • the present invention relates to the field of thermal machines. It relates to a method for repairing a local damage in the heat protection coating of a component according to the preamble of claim 1.
  • the multilayer heat protection coating usually comprises an adhesive layer applied to the base material (Bond Coating BC) and the actual heat protection layer (Thermal Barrier Coating TBC), which usually comprises a ceramic (eg columnar) Material exists.
  • a thermally grown oxide layer (Thermally Grown Oxide TGO) forms at the boundary between the adhesive layer and the heat protection layer, which protects the adhesion layer against further oxidation and corrosion and further improves the adhesion of the heat protection layer.
  • the object is solved by the entirety of the features of claim 1.
  • the essence of the invention is that, prior to the direct application of a ceramic filling layer, the metallic adhesive layer is first removed to a predetermined depth in order to restore defined ratios in the chemical composition of the adhesive layer. This makes it possible to realize the original mechanical properties of the heat protection coating in the field of repaired local damage.
  • a preferred embodiment of the inventive method is characterized in that the adhesive layer in the upper thickness range has a different chemical composition from the original, and that the predetermined depth is selected so that at least the thickness range of the adhesive layer is removed with the deviating chemical composition.
  • any residues of the heat protection layer and the oxide layer are first removed in a cleaning process in the region of the local damage prior to removal of the adhesion layer.
  • the thickness of the adhesive layer can be selectively reduced and unnecessary material removal is avoided, it is expedient that the removal of the adhesive layer, the remaining thickness is controlled. This is preferably done in that the thickness control the FSEC (F requency S canning E ddy C urrent) technique is used.
  • FSEC Frequency S canning E ddy C urrent
  • the ceramic filling layer is applied beyond the surface of the heat protection layer, and if the surface of the ceramic filling layer by mechanical processing, in particular grinding and / or Polishing, the surface of the heat protection layer is adjusted.
  • the inventive method can be carried out in particular on-site on built-in components. However, it can also be performed as part of service work or to repair new components.
  • the method is based on a made of a base material 11 component 10, for example a turbine blade or the like., Which is provided on the outer surface with a heat protection coating 12, 13, 14.
  • the heat protection coating 12, 13, 14 comprises a metallic bond coating 12 applied directly to the surface of the base material 11, and a ceramic thermal barrier coating (TBC) 14 arranged above the adhesion layer 12.
  • TBC ceramic thermal barrier coating
  • TBO thermally grown oxide
  • the heat protection coating 12, 13, 14 has now according to Fig. 1 a local damage 15, which consists essentially in a local flaking of the ceramic heat protection layer 14.
  • the heat protective layer 14 is completely chipped, while the oxide layer 13 and the underlying metallic adhesive layer 12 are virtually intact.
  • other configurations of local damage can certainly also be envisaged, in which, for example, parts of the heat protection layer 14 are still present, or the layers 13 and 12 are partially damaged.
  • any remnants of the ceramic heat protection layer 14 as well as the underlying oxide layer 13 or its residues are removed by means of a suitable material removal process.
  • the removal of material preferably takes place through suitable masks 18, which ensure that the lateral extent of the material removal is limited and defined.
  • the use of masks 18 results in uniformly beveled edge regions on the layers 12, 13, 14, which are advantageous for the adhesion of the later filled material.
  • the underlying metallic adhesion layer 12 is removed within the material removal 16 to a predetermined depth ( Fig. 2 ).
  • the predetermined depth of the removal of the adhesive layer 12 depends on how far into the depth the chemical composition of the adhesive layer 12 has changed compared to the original chemical composition due to surface processes such as the formation of the oxide layer 13. If the chemical composition of the adhesion layer 12 has changed, for example, in the upper half of the layer thickness, slightly more than half of the adhesion layer 12 is removed in order to ensure that the surface of the adhesion layer 12 emerging after the removal has the original chemical composition.
  • test method which is known as FSECT (Frequency Scanning Eddy Current) technique and evaluates the formation of induced eddy currents in an electrically conductive multi-layer composite as a function of the induction frequency.
  • the result is a layer composite 11, 12, 17 which has substantially the same mechanical properties as the original layer composite 11, 12, 14 prior to the formation of the oxide layer 13.
  • the repair method described can be done without difficulty to repair local damage to built-in components "on site". However, it is also conceivable to carry out the method as part of service work or to repair new components.

Claims (8)

  1. Procédé de réparation d'un dommage local (15) au revêtement barrière thermique d'un composant (10), le revêtement barrière thermique comprenant une couche métallique adhérente (12) et une couche barrière thermique (14) en céramique appliquée sur la couche métallique adhérente (12),
    le dommage local (15) ayant été provoqué par un aplatissement local de la couche barrière thermique (14),
    caractérisé en ce que
    dans une première étape, la couche métallique adhérente (12) est enlevée jusqu'à une profondeur prédéterminée, au moins la partie supérieure de l'épaisseur de la couche métallique adhérente (12) dans laquelle la composition chimique de la couche adhérente (12) diffère de la composition chimique initiale de la couche adhérente (12) étant enlevée et
    en ce que dans une deuxième étape, une couche céramique de rechargement (17) est appliquée sur la couche adhérente (12) d'épaisseur réduite pour compléter la couche barrière thermique (14).
  2. Procédé selon la revendication 1, caractérisé en ce qu'une couche d'oxyde (13) obtenue par croissance thermique est formée entre la couche adhérente (12) et la couche barrière thermique (14) qui la recouvre et en ce qu'avant l'enlèvement de la couche adhérente (12), les éventuels restes de couche barrière thermique (14) et d'une couche d'oxyde (13) sont enlevés au cours de l'opération de nettoyage de la zone occupée par le dommage local (15).
  3. Procédé selon l'une des revendications 1 à 2, caractérisé en ce que l'épaisseur restante est contrôlée lors de l'enlèvement de la couche adhérente (12).
  4. Procédé selon la revendication 3, caractérisé en ce que pour le contrôle de l'épaisseur, il utilise la technique FSEC ("Frequency Scanning Eddy Current" - balayage de fréquence des courants de Foucault).
  5. Procédé selon l'une des revendications 1 à 4, caractérisé en ce que l'enlèvement des couches (12, 13) et/ou le rechargement de la couche barrière thermique (14) s'effectuent à travers des masques (18, 19) appropriés pour former une bordure définie.
  6. Procédé selon l'une des revendications 1 à 5, caractérisé en ce que dans la deuxième étape, la couche de rechargement (17) en céramique est appliquée sur la surface (20) de la couche barrière thermique (14) et en ce que la surface de la couche de rechargement (17) en céramique est égalisée par usinage mécanique.
  7. Procédé selon l'une des revendications 1 à 6, caractérisé en ce que le procédé est exécuté in situ sur les composants (10) montés.
  8. Procédé selon la revendication 5, caractérisé en ce que les bordures des masques (18, 19) utilisés pour l'enlèvement des couches (12, 13) et/ou pour le rechargement de la couche barrière thermique (14) sont chanfreinées uniformément.
EP04101783A 2004-04-28 2004-04-28 Procédé de réparation d'une dégradation locale d'un revêtement de barrière thermique d'une pièce Expired - Lifetime EP1591549B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP04101783A EP1591549B1 (fr) 2004-04-28 2004-04-28 Procédé de réparation d'une dégradation locale d'un revêtement de barrière thermique d'une pièce
DE502004010936T DE502004010936D1 (de) 2004-04-28 2004-04-28 Verfahren zum Ausbessern einer lokalen Beschädigung in der Hitzeschutzbeschichtung eines Bauteils
AT04101783T ATE462023T1 (de) 2004-04-28 2004-04-28 Verfahren zum ausbessern einer lokalen beschädigung in der hitzeschutzbeschichtung eines bauteils

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04101783A EP1591549B1 (fr) 2004-04-28 2004-04-28 Procédé de réparation d'une dégradation locale d'un revêtement de barrière thermique d'une pièce

Publications (2)

Publication Number Publication Date
EP1591549A1 EP1591549A1 (fr) 2005-11-02
EP1591549B1 true EP1591549B1 (fr) 2010-03-24

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EP04101783A Expired - Lifetime EP1591549B1 (fr) 2004-04-28 2004-04-28 Procédé de réparation d'une dégradation locale d'un revêtement de barrière thermique d'une pièce

Country Status (3)

Country Link
EP (1) EP1591549B1 (fr)
AT (1) ATE462023T1 (fr)
DE (1) DE502004010936D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10494926B2 (en) 2017-08-28 2019-12-03 General Electric Company System and method for maintaining machines

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1645652A1 (fr) * 2004-10-07 2006-04-12 Siemens Aktiengesellschaft Procédé de fabrication d'un système de couches
US8221825B2 (en) 2009-03-30 2012-07-17 Alstom Technology Ltd. Comprehensive method for local application and local repair of thermal barrier coatings
US10927684B2 (en) * 2016-02-08 2021-02-23 Raytheon Technologies Corporation Repairing a coating with a pre-configured coating patch
US10717166B2 (en) 2016-12-02 2020-07-21 General Electric Company Motorized apparatus for use with rotary machines
DE102019207479A1 (de) * 2019-05-22 2020-11-26 Siemens Aktiengesellschaft Verfahren zur Durchführung von Servicemaßnahmen an einer Energieumwandlungsanlage und Energieumwandlungsanlage

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5723078A (en) * 1996-05-24 1998-03-03 General Electric Company Method for repairing a thermal barrier coating
US6235352B1 (en) * 1999-11-29 2001-05-22 Electric Power Research Institute, Inc. Method of repairing a thermal barrier coating
US6413578B1 (en) * 2000-10-12 2002-07-02 General Electric Company Method for repairing a thermal barrier coating and repaired coating formed thereby

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10494926B2 (en) 2017-08-28 2019-12-03 General Electric Company System and method for maintaining machines

Also Published As

Publication number Publication date
ATE462023T1 (de) 2010-04-15
EP1591549A1 (fr) 2005-11-02
DE502004010936D1 (de) 2010-05-06

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