EP1740738A1 - Verfahren zum aufbringen einer schützenden beschichtung auf ein thermisch beanspruchtes bauteil - Google Patents
Verfahren zum aufbringen einer schützenden beschichtung auf ein thermisch beanspruchtes bauteilInfo
- Publication number
- EP1740738A1 EP1740738A1 EP05742960A EP05742960A EP1740738A1 EP 1740738 A1 EP1740738 A1 EP 1740738A1 EP 05742960 A EP05742960 A EP 05742960A EP 05742960 A EP05742960 A EP 05742960A EP 1740738 A1 EP1740738 A1 EP 1740738A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer
- local damage
- layers
- component
- defect
- 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.)
- Granted
Links
Classifications
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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
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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
- 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
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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
- C23C28/34—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
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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
- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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 machines and components which are subjected to high thermal stress in use and which are provided with a thermal barrier coating or metallic protective layer. In particular, it relates to a method for repairing damaged areas on these layers.
- the multi-layer thermal insulation layer comprises an adhesive layer (Bond Coating BC) applied to the base material and the actual thermal insulation layer (Thermal Barrier Coating TBC), which usually consists of a ceramic material.
- a thermally grown oxide layer (Thermally Grown Oxide TGO) forms on the boundary between the adhesive layer and the thermal insulation layer, which protects the adhesive layer against further oxidation and corrosion and further improves the adhesion of the thermal insulation layer for a certain service life.
- the protective coating may flake off (as well as consumption, for example due to erosion) of the protective coating, which must then be repaired as quickly and reliably as possible to ensure operation resume as quickly as possible and be able to maintain it undisturbed for as long as possible.
- the sequence of the layers of the protective coating must be successively built up again, so that the component is again fully protected.
- a component that is otherwise provided with a protective coating has defects that are free of protective coatings, e.g. Weld seams or the like are present, which must subsequently be provided locally with a protective coating in the form of a metallic protective layer or a ceramic thermal insulation layer.
- EP-B1-0 808 913 discloses a method for repairing a ceramic thermal barrier coating. Further repair methods can be found in 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, US- A-6,605,364, EP1304446A1 and US 5,972,424).
- the known repair methods for protective coatings have the following problems: It is in the nature of the metallic protective layers or BC / TBC multilayer systems that the edges of the damaged or chipped areas have any shape without a specific shape. So far, no classification of the damage as a prerequisite for a decision about the repairability and the use of a corresponding standardized preparation of the damage location has been proposed. Areas that have been damaged during operation in the metallic protective layer or the BC / TBC multilayer system, but which do not appear visibly, cannot be recognized with the known methods and therefore cannot be repaired. This results in a high risk of component failure, even if the coating has been touched up locally. In order to be able to guarantee a full life cycle, the mechanical coated integrity of the entire coated surface or especially the areas at risk, i.e.
- the method should be able to be carried out on site on components installed in the machine (on-site) and on components removed from the machine (off-site).
- the object is achieved by the entirety of the features of claim 1.
- the essence of the invention is, in the pretreatment of the areas to be processed, to process the edge regions of the layers ending at the local damage or defect such that the layers in the edge regions are gradually removed by the extent of the removed surface of the individual layers of the outermost layer of the component down to the surface of the base material is gradually reduced and a mask of the appropriate size is used to determine the size of the surface to be removed from each layer.
- the edge areas of the individual layers are thus processed one after the other by removing each layer using a mask assigned to it.
- the new layers are applied by masks corresponding to the size of the removed layer in order to replenish the damaged area.
- the use of masks of different sizes one after the other avoids overlapping of the applied layers with the existing, adjacent layers.
- the masks allow the lateral extent of the applied layer areas to be limited in such a way that the applied layers at the edge do not significantly overlap the existing layers and so on
- the masks used in the application of the layers have mask openings which gradually increase in the same way as is the case with the masks for processing.
- the individual layers in the edge regions of the local damage are preferably removed in such a way that the ends of the individual layers are chamfered uniformly.
- a uniform beveling of the layer ends is achieved, for example, using a sandblasting process.
- the extent of the bevel ie the angle of the bevel relative to the surface normal, depends on the sandblasting parameters and the material parameters of the layers to be removed.
- the bevel forms an angle relative to the surface normal in a range from 30 ° to 75 °, preferably from 60 °.
- the bevel achieved is uniform in that the angle of the bevel within a layer and over the entire circumference of the damaged area is essentially the same, that is to say insofar as it can be achieved by a sandblasting process or other blasting process.
- the evenly beveled edge areas thus gradually move outwards and backwards in the course of the layer sequence from bottom to top, i.e.
- the grading of the layer removal provides the advantage that when applying the corresponding new layers in order to fill up the damaged area, overlaps from layer to layer are avoided and new layer material is only applied to the layer intended for this and does not reach the subsequent layer.
- the bevelled ends of the layers offer the additional advantage of improved adhesion of the newly applied layers.
- a sufficiently wide area of the layers ending at the local damage or defect is preferably removed in order to be able to reliably rule out irregularities in the critical edge areas.
- the areal extent of the damaged area that needs to be repaired is thus determined.
- the depth of the damaged area is also determined, i.e. which parts of the layered composite have to be repaired, such as only TBC or TBC / BC or TBC / BC / BM.
- the extent of the area selected for repair and the presence of hidden damage areas are determined, for example, by a non-destructive method such as the FSECT (Frequency Scanning Eddy Current technology).
- Masks with a rounded, in particular circular, mask opening are preferably used.
- the use of such a mask shape in contrast to a shape with corners, avoids stresses that could arise from pointed corners.
- a particularly high quality of the repaired or filled area results if, within the second step, before the application of a layer, the surface of the layer underneath to improve the adhesion of the processed layer to be applied, for example roughened. This is preferably done using sandblasting or blasting with ceramic blasting material.
- the surface is worked on in the area of the previous local damage or flaw to remove unevenness, this preferably using grinding and / or polishing takes place.
- thermography In order to obtain reliable information about the success of a repair, it is advantageous if after the local damage or defect has been eliminated, the area of the previous local damage or defect is subjected to a quality check. This is preferably done using non-destructive methods, in particular thermography or FSECT (Frequency Scanning Eddy Current technology).
- the method according to the invention has proven itself in a coating which is a thermal barrier coating system which comprises an adhesive layer applied to the base material and a thermal barrier coating applied to the adhesive layer.
- the method is advantageously carried out on-site on built-in components, small, portable processing systems, in particular for cleaning and plasma spraying, being used to process the local damage or defect. Likewise, the process is of course also suitable for off-site repairs to removed components.
- the method according to the invention is suitable both for components which have been damaged during operation and for new components which have been damaged, for example, during assembly or during transport. So that a component can be fully treated within the scope of the method according to the invention, it is advantageous if the surface of the component is first checked for its mechanical integrity, at least in particularly vulnerable areas, such as the pressure side and front edge of turbine blades, using a non-destructive test method examined and the areas to be repaired identified and their extent determined.
- the FSECT Frequency Scanning Eddy Current technology
- FIG. 1 shows a photographic representation of the top view of a cleaned local damage to a component or substrate provided with a thermal insulation layer and prepared for the new coating by the method according to the invention
- FIG. 2 shows the component from FIG. 1 after the new coating and final treatment of the surface
- FIG. 3 shows a schematic, perspective representation of the use of a typical mask for the pretreatment and re-coating of a local damage or defect
- FIG. 4 shows a micrograph of a repaired local damage with an overlap of the renewed adhesive layer that occurs due to a lack of masking, which would be avoided by the method according to the invention; 5 shows an enlarged representation of the micrograph from FIG. 4;
- Fig. 6 is a micrograph of an overlap of the renewed adhesive layer along a beveled edge of the thermal insulation layer, which results when working with or with unsuitable masks.
- 7 shows different steps in different partial figures for the repair on-site or off-site of local damage to a component which is subject to operational stress and is provided with a thermal insulation layer, according to a preferred exemplary embodiment of the method according to the invention.
- FIG. 8 shows different steps in different partial figures in the local application on-site or off-site of a new thermal insulation layer for the purpose of refilling a damaged area or a local defect.
- a first step in repairing a damaged metallic or BC TBC coating on the base material of a component involves classifying the defects into specific categories, followed by the decision as to which defective coating subarea and which standardized methods can be repaired. For this purpose, the entire coated surface of the component or at least the particularly vulnerable areas are examined for their mechanical integrity using non-destructive testing methods.
- the FSECT Frequency Scanning Eddy Current Technology
- the im Component-induced eddy currents depending on the frequency are examined and evaluated.
- masks 21 of the type shown in FIG. 3 are selected, the mask openings 22 of which correspond to the extent of the defect.
- the mask openings encompass the size of the obvious damaged area as well as other areas around this obvious damaged area that have been assessed as damaged due to a non-destructive inspection (including a safety surcharge).
- the size of the mask opening 22 is selected such that, for safety reasons, an edge region of sufficient width is always removed from the layer to be removed in order to safely remove all damaged areas without, however, impairing the undamaged areas of the layer.
- the masks 21 are placed on the substrate or component 20, whereupon the damaged coating is successively removed through the mask opening 22.
- Masks 21 with mask openings 22 of different sizes, more precisely with successively smaller sizes, are used in succession in order to remove the metallic protective layer or the TBC layer, the BC layer and any oxidized base material of the substrate.
- a new step or “terrace level” is generated for each layer.
- the resulting steps are shown in FIG. 7b.
- the method can also be carried out by successively increasing the size of the masks used, that is to say the smallest 1, 7 and 8, uniformly beveled edge areas 16 are generated when using sandblasting as the removal method. These are for the subsequent repair or filling process, in particular for the adhesion of the newly applied layers, crucial.
- FIGS. 4, 5 and 6 show, in different enlargements, micrographs of an edge overlap 25 of a subsequently applied 5th adhesive layer 17, which leads to the ceramic thermal insulation layer 13 lying above undergoing a mechanical weakening there.
- 6 shows an overlap 25 at an oblique edge region of the thermal insulation layer 13, which also leads to a mechanical weakening.
- FIG. 7a in order 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 insulation layer 13, which has local damage 14, is applied.
- the individual layers 11, 12 and 13 have irregularly formed edge regions 15 in the area of the local damage 14.
- the irregular steps become in a first step through suitable masks 23 according to FIG.
- Edge regions 15 of the layers are successively removed, so that all layers 11, 12, 13 have uniformly beveled 5 edge regions 16 which border an opening in the layer sequence with an increasing diameter towards the outside. Only one mask 23 is shown in FIG. 7b.
- the individual layers 11, 12, 13 are removed one after the other in partial steps using a mask that is matched to the layer, so that at least 3 masks 23 are used in the 3 layers 11, 12, 130.
- a first mask is used with a size of the largest opening, ie the opening 14 on the upper surface of the Layer 13. It is then removed to the surface of layer 12.
- the next mask has an opening with a slightly smaller size, ie the opening 14 on the upper surface of the layer 12. It is then removed up to the surface of the layer 12.
- the next mask is again smaller with an opening equal to the opening 14 on the surface of the layer 11.
- the staggered removal of the individual layers to produce a terrace-shaped opening 14 as in FIG. 7b can also be carried out in reverse order of size by using the masks mentioned, starting with the smallest mask and ending with the largest mask.
- FIG. 7c shows the addition of the adhesive layer 11 by a renewed adhesive layer 17, which is done through a mask 24 to avoid overlaps.
- a renewed thermal insulation layer 18 is also applied (FIG. 7d), which is then adapted by grinding and / or polishing the remaining surface (FIG. 7e). If the component 200 repaired in this way is exposed to high temperatures, a newly grown oxide layer 19 is formed (FIG. 7e), so that the original layer sequence is completely restored.
- FIG. 7 relates to the repair of local damage 14
- different partial figures in FIG. 8 show different steps in the application of a new thermal barrier coating for refilling a local fault 14 'of a component provided with a BC / TBC thermal barrier coating system 300 reproduced.
- a local flaw 14 ' occurs, for example, in the area of a weld seam when two previously coated parts are welded together. Since such a component 300 has to be processed before the first use in order to complete the thermal insulation layer, there is still no thermally grown oxide layer in the layer sequence here (FIG. 8a). In this case too, the irregular edge regions 15 of FIG Layers 11, 13 are transferred into evenly beveled edge regions 16 by targeted removal (FIG. 8b).
- the layers 17 and 18 are newly applied through appropriate masks 24 (FIGS. 8c and d) and adapted to the surface (FIG. 8e).
- plasma spraying or a spraying process which brings the material to be applied into a molten or melted phase, it is achieved that the new layers 17, 18, the openings 14 'are applied corresponding to the mask opening.
- FIGS. 1 and 2 A photographic representation of local damage to a component 100 before the layers are applied and after the repair is shown in FIGS. 1 and 2.
- 1 shows a top view from above of the pretreated local damage 14 with the exposed base material 10, the adhesive layer 11 and the thermal insulation layer 13.
- FIG. 3 shows the surface of the renewed thermal insulation layer 18 adapted by grinding after the repair (comparable to FIGS. 7e & 8e).
- Local damage 14 or defects 14 ' are preferably processed on the built-in component “on site”, blasting processes with ceramic blasting material or sandblasting being used for cleaning (& similar blasting processes) and ablation, and spraying processes for applying the new layers the material to be applied is brought into a molten or melted state, for example by means of the plasma, micro-plasma, laser or HVOF process
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- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Physics & Mathematics (AREA)
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Abstract
Description
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Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP05742960A EP1740738B1 (de) | 2004-04-28 | 2005-04-20 | Verfahren zum aufbringen einer schützenden beschichtung auf ein thermisch beanspruchtes bauteil |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP04101784A EP1591561A1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum Aufbringen einer schützenden Beschichtung auf ein thermisch beanspruchtes Bauteil |
| PCT/EP2005/051748 WO2005106075A1 (de) | 2004-04-28 | 2005-04-20 | Verfahren zum aufbringen einer schützenden beschichtung auf ein thermisch beanspruchtes bauteil |
| EP05742960A EP1740738B1 (de) | 2004-04-28 | 2005-04-20 | Verfahren zum aufbringen einer schützenden beschichtung auf ein thermisch beanspruchtes bauteil |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1740738A1 true EP1740738A1 (de) | 2007-01-10 |
| EP1740738B1 EP1740738B1 (de) | 2011-03-30 |
Family
ID=34929029
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP04101784A Withdrawn EP1591561A1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum Aufbringen einer schützenden Beschichtung auf ein thermisch beanspruchtes Bauteil |
| EP05742960A Expired - Lifetime EP1740738B1 (de) | 2004-04-28 | 2005-04-20 | Verfahren zum aufbringen einer schützenden beschichtung auf ein thermisch beanspruchtes bauteil |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP04101784A Withdrawn EP1591561A1 (de) | 2004-04-28 | 2004-04-28 | Verfahren zum Aufbringen einer schützenden Beschichtung auf ein thermisch beanspruchtes Bauteil |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US7544520B2 (de) |
| EP (2) | EP1591561A1 (de) |
| KR (1) | KR101168184B1 (de) |
| AT (1) | ATE503863T1 (de) |
| CA (1) | CA2564172C (de) |
| DE (1) | DE502005011190D1 (de) |
| MX (1) | MXPA06012427A (de) |
| WO (1) | WO2005106075A1 (de) |
Families Citing this family (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1591561A1 (de) | 2004-04-28 | 2005-11-02 | ALSTOM (Switzerland) Ltd | Verfahren zum Aufbringen einer schützenden Beschichtung auf ein thermisch beanspruchtes Bauteil |
| 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 |
| SG163533A1 (en) * | 2006-12-29 | 2010-08-30 | Gen Electric | Method for restoring or regenerating an article and restored or regenerated article |
| 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 |
| EP2628816A1 (de) * | 2012-02-14 | 2013-08-21 | Siemens Aktiengesellschaft | Verfahren zum Aufbringen einer Wärmedämmschicht |
| US9290836B2 (en) * | 2012-08-17 | 2016-03-22 | General Electric Company | Crack-resistant environmental barrier coatings |
| CN105189931B (zh) * | 2013-03-15 | 2017-05-24 | 西门子能源公司 | 使用钎焊表面纹理化的超合金箔进行的部件修复 |
| 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 |
| GB202311067D0 (en) * | 2023-07-19 | 2023-08-30 | Rolls Royce Plc | A method of manufacturing a component of a gas turbine engine |
| DE102024205658A1 (de) | 2024-06-19 | 2025-12-24 | Siemens Energy Global GmbH & Co. KG | Verfahren zur Reparatur einer Beschichtung eines Heißgasbauteils |
Family Cites Families (17)
| 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 |
| US5723078A (en) * | 1996-05-24 | 1998-03-03 | General Electric Company | Method for repairing a thermal barrier coating |
| 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 |
| US20020076573A1 (en) * | 2000-12-19 | 2002-06-20 | Neal James Wesley | Vapor deposition repair of superalloy articles |
| US6465040B2 (en) | 2001-02-06 | 2002-10-15 | General Electric Company | Method for refurbishing a coating including a thermally grown oxide |
| JP3905724B2 (ja) * | 2001-06-13 | 2007-04-18 | 三菱重工業株式会社 | Ni基合金製部品の補修方法 |
| 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 |
| 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 (de) | 2004-04-28 | 2005-11-02 | ALSTOM (Switzerland) Ltd | Verfahren zum Aufbringen einer schützenden Beschichtung auf ein thermisch beanspruchtes Bauteil |
| US7309512B2 (en) | 2006-04-04 | 2007-12-18 | Siemens Power Generation, Inc. | Method of repairing an article having a bondcoat and a topcoat |
-
2004
- 2004-04-28 EP EP04101784A patent/EP1591561A1/de not_active Withdrawn
-
2005
- 2005-04-20 AT AT05742960T patent/ATE503863T1/de active
- 2005-04-20 EP EP05742960A patent/EP1740738B1/de not_active Expired - Lifetime
- 2005-04-20 MX MXPA06012427A patent/MXPA06012427A/es active IP Right Grant
- 2005-04-20 CA CA2564172A patent/CA2564172C/en not_active Expired - Fee Related
- 2005-04-20 DE DE502005011190T patent/DE502005011190D1/de not_active Expired - Lifetime
- 2005-04-20 KR KR1020067022512A patent/KR101168184B1/ko not_active Expired - Fee Related
- 2005-04-20 WO PCT/EP2005/051748 patent/WO2005106075A1/de not_active Ceased
-
2006
- 2006-10-27 US US11/553,748 patent/US7544520B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
| Title |
|---|
| See references of WO2005106075A1 * |
Also Published As
| Publication number | Publication date |
|---|---|
| MXPA06012427A (es) | 2007-01-17 |
| US20070063351A1 (en) | 2007-03-22 |
| WO2005106075A1 (de) | 2005-11-10 |
| KR101168184B1 (ko) | 2012-07-25 |
| CA2564172C (en) | 2012-06-12 |
| ATE503863T1 (de) | 2011-04-15 |
| DE502005011190D1 (de) | 2011-05-12 |
| US7544520B2 (en) | 2009-06-09 |
| EP1740738B1 (de) | 2011-03-30 |
| CA2564172A1 (en) | 2005-11-10 |
| EP1591561A1 (de) | 2005-11-02 |
| KR20070010033A (ko) | 2007-01-19 |
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