EP1591561A1 - Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température - Google Patents

Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température Download PDF

Info

Publication number
EP1591561A1
EP1591561A1 EP04101784A EP04101784A EP1591561A1 EP 1591561 A1 EP1591561 A1 EP 1591561A1 EP 04101784 A EP04101784 A EP 04101784A EP 04101784 A EP04101784 A EP 04101784A EP 1591561 A1 EP1591561 A1 EP 1591561A1
Authority
EP
European Patent Office
Prior art keywords
layers
defect
local damage
layer
masks
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.)
Withdrawn
Application number
EP04101784A
Other languages
German (de)
English (en)
Inventor
Stefan Kiliani
Alexander Stankowski
Frigyes Szücs
Thomas Duda
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 Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to EP04101784A priority Critical patent/EP1591561A1/fr
Priority to KR1020067022512A priority patent/KR101168184B1/ko
Priority to AT05742960T priority patent/ATE503863T1/de
Priority to MXPA06012427A priority patent/MXPA06012427A/es
Priority to PCT/EP2005/051748 priority patent/WO2005106075A1/fr
Priority to CA2564172A priority patent/CA2564172C/fr
Priority to EP05742960A priority patent/EP1740738B1/fr
Priority to DE502005011190T priority patent/DE502005011190D1/de
Publication of EP1591561A1 publication Critical patent/EP1591561A1/fr
Priority to US11/553,748 priority patent/US7544520B2/en
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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
    • C23C4/18—After-treatment
    • 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
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the present invention relates to the field of thermal Machinery. It relates to a method for applying a thermal barrier coating or a metallic protective layer on a thermally stressed, from a base material existing component according to the preamble of the claim 1.
  • the multi-layer thermal barrier coating comprises an adhesive layer applied to the base material (bond coating BC) and the actual Thermal Barrier Coating (TBC), the usually consists of a ceramic material.
  • bond coating BC the actual Thermal Barrier Coating
  • TBC Thermal Barrier Coating
  • the adhesive layer protects against further oxidation and corrosion and adhesion the thermal barrier further improved.
  • EP-B1-0 808 913 discloses a method of repairing a ceramic thermal barrier coating. Further repair methods are known from the documents US-A-5,735,448, US-A-6,042,880, US-A-6,203,847, US-A-6,235,352, US-A-6,274,193, US-A-6,305,077, US-A-6,465,040 and US-A-6,605,364.
  • It is an object of the invention to provide a method for repairing local Damage or filling of local defects indicate which the Disadvantages of known methods avoids and in particular by a high Quality and resilience of the machined areas are distinguished and on site can be carried out.
  • the object is solved by the entirety of the features of claim 1.
  • the essence of the invention is in the pretreatment of working areas, the edge areas at the local damage or To repair flaw-ending layers in such a way that they are uniform form bevelled edge regions.
  • the evenly bevelled Edge areas which are in the course of the layer sequence from bottom to top increasingly withdraw to the outside, pose for the subsequently applied Layers due to their shape and regularity a basis for optimal adaptation in a critical area.
  • the processing of the edge regions of the layers takes place successively through the masks associated with respective layers.
  • a special high quality of the repaired or filled area results if, within the second step, before applying a layer the surface of the underlying layer to improve the adhesion of the applied layer, e.g. is roughened. this happens preferably by sandblasting.
  • the surface in the area of the former local damage or defect is repaired to remove bumps, this being preferably by means of grinding and / or polishing.
  • thermography F requency S canning E ddy C urrent
  • the represents a thermal barrier coating system, which one on the base material applied adhesive layer and one applied to the adhesive layer Thermal insulation layer comprises.
  • the method is locally on built-in components performed, where to edit the local damage or defect small, portable processing systems, in particular for cleaning and Plasma spraying, to be used.
  • the surface of the component is first examined for its mechanical integrity by means of a non-destructive testing method, at least in particularly endangered areas, thereby identifying the areas to be repaired and identifying them Extension.
  • the FSEC Frequency S canning E ddy C urrent
  • a first step in repairing a damaged metallic or BC / TBC coating on the base material of a component involves classifying the defects into particular categories, followed by deciding whether and with what standardized methods the defects can be treated. For this purpose, the entire coated surface of the component or at least the most vulnerable areas are examined for their mechanical integrity by means of nondestructive testing methods.
  • a non-destructive test method it is in particular the FSEC (F requency S canning E ddy C urrent) technology into consideration, in which the induced in the surface region of the component, eddy currents are studied as a function of frequency and analyzed.
  • masks become 21 of the type shown in Fig. 3 selected the mask openings 22 of the Extension of the defect accordingly.
  • the masks 21 are applied to the substrate or component 20 is placed and through the mask opening 22 through the damaged coating successively removed.
  • the size of the mask opening 22 is chosen so that in the ablated layer from For safety reasons, always an edge area of sufficient width is removed, to remove all damaged areas safely, but without the undamaged areas of the layer. It will be successively Masks 21 with different sized mask openings 22 used to the metallic protective layer or the TBC layer, the BC layer and any to remove oxidized base material of the substrate. With the use of Masks 21 are evenly chamfered in the respective layers Edge regions (16 in Fig. 1, 7 and 8) generated for the subsequent Correction or refilling process are crucial.
  • Figs. 4, 5 and 6 show in different Enlargement of micrographs of a marginal overlap 25 one after the other applied adhesive layer 17, which causes the overlying ceramic thermal barrier coating 13 there undergoes a mechanical weakening.
  • Fig. 6 shows an overlap 25 at an oblique edge region of Thermal insulation layer 13, which also leads to a mechanical weakening.
  • Fig. 7 different steps in the various subfigures in the Mending location of a local damage one with a BC / TBC thermal barrier coating system provided component 200 according to a preferred embodiment of the inventive method played.
  • Fig. 7a is to protect the component 200 on the Base material 10 of the component 200, a layer sequence of an adhesive layer 11, a thermally grown oxide layer 12 and a ceramic Thermal barrier layer 13 is applied, which has a local damage 14.
  • the individual layers 11, 12 and 13 point in the region of the local Damage 14 irregularly shaped edge regions 15 on.
  • Fig. 7b If the local damage 14 is detected and selected for repair, 7b in a first step by suitable masks 23rd through the irregular edge regions 15 of the layers successively removed, so that all layers 11, 12, 13 evenly beveled Edge regions 16 having an opening in the layer sequence with after outside of increasing diameter.
  • Fig. 7b is only a mask 23rd located.
  • the individual layers 11, 12, 13 in Sub-steps one after the other using one on the layer matched mask, so that in the 3 layers 11, 12, 13 at least 3 masks 23 are used.
  • Fig. 7c is the Supplementing the adhesive layer 11 by a renewed adhesive layer 17 shown to Avoiding overlaps through a mask 24 happens.
  • a renewed thermal barrier coating 18 is applied (Fig. 7d), which are then adjusted by grinding and / or polishing the remaining surface becomes (Fig. 7e). If the component 200 thus repaired is exposed to high temperatures, a newly grown oxide layer 19 (FIG. 7e) forms, so that the original layer sequence is completely restored.
  • FIG. 7 relates to the repair of a local damage 14
  • FIG. 8 in different sub-figures, different steps in the Repairing a Local Fault 14 'One with a BC / TBC Thermal Barrier System provided component 300 reproduced.
  • a such local defect 14 'results for example, in the range of Welded seam, if two previously coated parts with each other be welded. Since such a component 300 even before the first use must be machined to complete the thermal barrier coating is in the layer sequence here no thermally grown oxide layer present (Figure 8a).
  • Figure 8c and d first by masks 23 through the irregular edge regions 15 of the layers 11, 13 by targeted removal converted into uniformly bevelled edge regions 16 (FIG. 8b). Then be through corresponding masks 24 through the layers 17 and 18 new applied ( Figures 8c and d) and adapted to the surface ( Figure 8e).
  • FIG. 1 shows in plan view from above the pretreated local Damage 14 with the exposed base material 10, the adhesive layer 11 and the thermal barrier coating 13.
  • Fig. 3 Art shows by grinding adapted surface of the renewed thermal barrier coating 18 after the Repair (comparable to Fig. 7e).
  • the processing of the local damage 14 or defects 14 'takes place preferably on the built-in component "on site", wherein for cleaning, ablation the old and applying the new layers plasma, micro-TIG, micro-plasma, Laser, MIG or HVOF processes are used.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Inorganic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)
  • Electronic Switches (AREA)
  • Magnetic Heads (AREA)
EP04101784A 2004-04-28 2004-04-28 Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température Withdrawn EP1591561A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP04101784A EP1591561A1 (fr) 2004-04-28 2004-04-28 Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température
KR1020067022512A KR101168184B1 (ko) 2004-04-28 2005-04-20 열 응력이 가해진 컴포넌트에 보호 코팅을 도포하는 방법
AT05742960T ATE503863T1 (de) 2004-04-28 2005-04-20 Verfahren zum aufbringen einer schützenden beschichtung auf ein thermisch beanspruchtes bauteil
MXPA06012427A MXPA06012427A (es) 2004-04-28 2005-04-20 Metodo para la aplicacion de un revestimiento protector a un componente termicamente tensado.
PCT/EP2005/051748 WO2005106075A1 (fr) 2004-04-28 2005-04-20 Procede pour appliquer un revetement protecteur sur une piece exposee a des contraintes thermiques
CA2564172A CA2564172C (fr) 2004-04-28 2005-04-20 Procede pour appliquer un revetement protecteur sur une piece exposee a des contraintes thermiques
EP05742960A EP1740738B1 (fr) 2004-04-28 2005-04-20 Procede pour appliquer un revetement protecteur sur une piece exposee a des contraintes thermiques
DE502005011190T DE502005011190D1 (de) 2004-04-28 2005-04-20 Verfahren zum aufbringen einer schützenden beschic
US11/553,748 US7544520B2 (en) 2004-04-28 2006-10-27 Method for the application of a protective coating to a thermally stressed component

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04101784A EP1591561A1 (fr) 2004-04-28 2004-04-28 Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température

Publications (1)

Publication Number Publication Date
EP1591561A1 true EP1591561A1 (fr) 2005-11-02

Family

ID=34929029

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04101784A Withdrawn EP1591561A1 (fr) 2004-04-28 2004-04-28 Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température
EP05742960A Not-in-force EP1740738B1 (fr) 2004-04-28 2005-04-20 Procede pour appliquer un revetement protecteur sur une piece exposee a des contraintes thermiques

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05742960A Not-in-force EP1740738B1 (fr) 2004-04-28 2005-04-20 Procede pour appliquer un revetement protecteur sur une piece exposee a des contraintes thermiques

Country Status (8)

Country Link
US (1) US7544520B2 (fr)
EP (2) EP1591561A1 (fr)
KR (1) KR101168184B1 (fr)
AT (1) ATE503863T1 (fr)
CA (1) CA2564172C (fr)
DE (1) DE502005011190D1 (fr)
MX (1) MXPA06012427A (fr)
WO (1) WO2005106075A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1950320A1 (fr) * 2006-12-29 2008-07-30 General Electric Company Procédé pour rétablir ou régénérer un article et article régénéré rétabli
EP2628816A1 (fr) * 2012-02-14 2013-08-21 Siemens Aktiengesellschaft Procédé d'application d'une couche isolante

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1591561A1 (fr) 2004-04-28 2005-11-02 ALSTOM (Switzerland) Ltd Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température
JP5019811B2 (ja) * 2006-07-20 2012-09-05 東京エレクトロン株式会社 静電吸着電極の補修方法
US20100254820A1 (en) * 2006-12-29 2010-10-07 Michael Patrick Maly Article with restored or regenerated structure
US8221825B2 (en) * 2009-03-30 2012-07-17 Alstom Technology Ltd. Comprehensive method for local application and local repair of thermal barrier coatings
US20120167389A1 (en) * 2011-01-04 2012-07-05 General Electric Company Method for providing a film cooled article
US9290836B2 (en) * 2012-08-17 2016-03-22 General Electric Company Crack-resistant environmental barrier coatings
EP2971563A2 (fr) * 2013-03-15 2016-01-20 Siemens Energy, Inc. Réparation de composants à l'aide d'une feuille en superalliage texturée à surface brasée
JP6234745B2 (ja) * 2013-09-09 2017-11-22 三菱重工業株式会社 皮膜補修方法及びこれを用いて皮膜が補修された部材
JP6234746B2 (ja) * 2013-09-09 2017-11-22 三菱重工業株式会社 皮膜補修方法
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
US10364701B2 (en) * 2016-12-06 2019-07-30 General Electric Company CMAS barrier coating for a gas turbine engine having a reactive material that reacts with a layer of environmental contaminant compositions and method of applying the same
US11067002B2 (en) 2016-12-06 2021-07-20 General Electric Company Gas turbine engine maintenance tool
US10494926B2 (en) 2017-08-28 2019-12-03 General Electric Company System and method for maintaining machines
SG10202010783RA (en) 2019-11-06 2021-06-29 Gen Electric Restoration coating system and method
US11753713B2 (en) 2021-07-20 2023-09-12 General Electric Company Methods for coating a component

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0808913A1 (fr) * 1996-05-24 1997-11-26 General Electric Company Procédé pour la réparation d'un revêtement de barrière thermique
EP1217090A1 (fr) * 2000-12-19 2002-06-26 United Technologies Corporation Procédé de dépôt en phase vapeur pour la réparation des articles en superalliage
US20030082297A1 (en) * 2001-10-26 2003-05-01 Siemens Westinghouse Power Corporation Combustion turbine blade tip restoration by metal build-up using thermal spray techniques
EP1408134A1 (fr) * 2001-06-13 2004-04-14 Mitsubishi Heavy Industries, Ltd. Procede pour reparer un composant en alliage a base de nickel

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2694131B1 (fr) 1992-07-21 1996-09-27 Balzers Hochvakuum Procede et installation pour la fabrication d'un composant, notamment d'un composant optique, et composant optique ainsi obtenu.
US5437737A (en) 1994-02-07 1995-08-01 United Technologies Corporation Repair coating for superalloy articles, such as gas turbine engine components
US5958166A (en) 1996-12-31 1999-09-28 Mcdonnell Douglas Corporation Method for repairing high temperature composite structures
US6042880A (en) 1998-12-22 2000-03-28 General Electric Company Renewing a thermal barrier coating system
US6203847B1 (en) 1998-12-22 2001-03-20 General Electric Company Coating of a discrete selective surface of an article
US6387527B1 (en) 1999-10-04 2002-05-14 General Electric Company Method of applying a bond coating and a thermal barrier coating on a metal substrate, and related articles
US6305077B1 (en) 1999-11-18 2001-10-23 General Electric Company Repair of coated turbine components
US6235352B1 (en) 1999-11-29 2001-05-22 Electric Power Research Institute, Inc. Method of repairing a thermal barrier coating
US6605364B1 (en) 2000-07-18 2003-08-12 General Electric Company Coating article and method for repairing a coated surface
US6465040B2 (en) 2001-02-06 2002-10-15 General Electric Company Method for refurbishing a coating including a thermally grown oxide
US6707297B2 (en) * 2002-04-15 2004-03-16 General Electric Company Method for in-situ eddy current inspection of coated components in turbine engines
EP1591561A1 (fr) 2004-04-28 2005-11-02 ALSTOM (Switzerland) Ltd Méthode pour l'application d'un revêtement protecteur sur une pièce soumettant à haute température
US7309512B2 (en) 2006-04-04 2007-12-18 Siemens Power Generation, Inc. Method of repairing an article having a bondcoat and a topcoat

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0808913A1 (fr) * 1996-05-24 1997-11-26 General Electric Company Procédé pour la réparation d'un revêtement de barrière thermique
EP1217090A1 (fr) * 2000-12-19 2002-06-26 United Technologies Corporation Procédé de dépôt en phase vapeur pour la réparation des articles en superalliage
EP1408134A1 (fr) * 2001-06-13 2004-04-14 Mitsubishi Heavy Industries, Ltd. Procede pour reparer un composant en alliage a base de nickel
US20030082297A1 (en) * 2001-10-26 2003-05-01 Siemens Westinghouse Power Corporation Combustion turbine blade tip restoration by metal build-up using thermal spray techniques

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1950320A1 (fr) * 2006-12-29 2008-07-30 General Electric Company Procédé pour rétablir ou régénérer un article et article régénéré rétabli
EP2628816A1 (fr) * 2012-02-14 2013-08-21 Siemens Aktiengesellschaft Procédé d'application d'une couche isolante

Also Published As

Publication number Publication date
EP1740738A1 (fr) 2007-01-10
WO2005106075A1 (fr) 2005-11-10
EP1740738B1 (fr) 2011-03-30
CA2564172A1 (fr) 2005-11-10
KR101168184B1 (ko) 2012-07-25
MXPA06012427A (es) 2007-01-17
US20070063351A1 (en) 2007-03-22
ATE503863T1 (de) 2011-04-15
DE502005011190D1 (de) 2011-05-12
CA2564172C (fr) 2012-06-12
US7544520B2 (en) 2009-06-09
KR20070010033A (ko) 2007-01-19

Similar Documents

Publication Publication Date Title
EP1740738B1 (fr) Procede pour appliquer un revetement protecteur sur une piece exposee a des contraintes thermiques
DE602006000803T2 (de) Verfahren zum Reparieren einer Schaufel einer integral beschaufelten Turbinenrotorscheibe und Prüfkörper zur Durchführung des Verfahrens
CN100546756C (zh) 修理单片叶片转盘的方法,起始和终了测试片
DE3730266C2 (fr)
DE69807892T2 (de) Verfahren zur herstellung eines durchbrochenen artikels zur wiederbeschichtung
EP2038083B1 (fr) Procédé de réparation et/ou de remplacement d'éléments individuels d'une pièce d'une turbine à gaz
DE3619536A1 (de) Verfahren zum reparieren eines metallgegenstandes, insbesondere einer labyrinthdichtung
EP1605068A2 (fr) Soudage homogène au moyen de préchauffage pour superalliage à haute résistance et dépôt de matière
EP2072176A1 (fr) Procédé destiné à la fabrication d'une couche de protection à base d'acier contre l'érosion utilisant le laser; Composant comprenant une telle couche de protection à base d'acier contre l'érosion
EP1771275A1 (fr) Procede pour reparer ou fabriquer un element constitutif
EP2591872A1 (fr) Procédé de refonte et de remplissage ultérieur et composant obtenu
DE102014204806A1 (de) Verfahren zur Neuherstellung von Durchgangslöchern in einem Schichtsystem
DE102010001414A1 (de) Verfahren zur Reparatur von Labyrinth-Dichtungsstegen
WO2009065385A1 (fr) Procédé de réparation d'un élément de turbine à gaz
EP1805344B1 (fr) Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure
DE10005874A1 (de) Schweissverfahren zur Rissreparatur
DE3325251A1 (de) Verfahren zum pruefen und nachbessern von auf bauelementen aufgetragenen schutzschichten
DE102011002532A1 (de) Verfahren zur Reparatur von Verdichter- oder Turbinentrommeln
DE102004002551B4 (de) Verfahren zur Reparatur von Bauteilen
EP1591549B1 (fr) Procédé de réparation d'une dégradation locale d'un revêtement de barrière thermique d'une pièce
EP2719494A1 (fr) Procédé adaptatif pour ouvrir des passages fermés d'un composant
DE8909840U1 (de) Gerät zum Reparieren oder Nachbearbeiten einer Turbinen- oder Kompressorschaufel
DE102020211954A1 (de) Verfahren zum Laserstrahlreinigen von Bauteiloberflächen sowie Laserstrahlreinigungseinrichtung
WO2005071227A1 (fr) Procede et dispositif de reparation de rotors a aubage integral
EP2832489A1 (fr) Procédé de réparation d'un crochet de réception pour des aubes directrices

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM TECHNOLOGY LTD

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20060503