EP1432847B1 - Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique - Google Patents

Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique Download PDF

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Publication number
EP1432847B1
EP1432847B1 EP02730264A EP02730264A EP1432847B1 EP 1432847 B1 EP1432847 B1 EP 1432847B1 EP 02730264 A EP02730264 A EP 02730264A EP 02730264 A EP02730264 A EP 02730264A EP 1432847 B1 EP1432847 B1 EP 1432847B1
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EP
European Patent Office
Prior art keywords
component
layer
cleaning agent
metal
corrosion products
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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
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EP02730264A
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German (de)
English (en)
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EP1432847A1 (fr
EP1432847B8 (fr
Inventor
Norbert Czech
Andre Jeutter
Adrian Kempster
Ralph Reiche
Rolf WILKENHÖNER
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Siemens AG En Diffusion Alloys Ltd
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Siemens AG
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Publication date
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Priority to EP02730264A priority Critical patent/EP1432847B8/fr
Publication of EP1432847A1 publication Critical patent/EP1432847A1/fr
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Publication of EP1432847B1 publication Critical patent/EP1432847B1/fr
Publication of EP1432847B8 publication Critical patent/EP1432847B8/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
    • 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
    • C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
    • C23G5/00—Cleaning or de-greasing metallic material by other methods; Apparatus for cleaning or de-greasing metallic material with organic solvents
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/90—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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment

Definitions

  • the invention relates to a method for removing one Layer region of a metal or a metal compound existing component, in which a multi-component Cleaning agent in a simple way to the component or the layer area is applied, which causes a heat treatment of the component with the cleaning agent the layer area easier to remove or remove.
  • ceramic thermal barrier coatings have been developed on thermally loaded components, eg. From Superalloys, are applied alone the high Inlet temperatures could not withstand in the long term.
  • the ceramic thermal barrier coating offers the advantage of a high temperature resistance due to their ceramic Properties and the metallic substrate offers the advantage the good mechanical properties in this composite or Layer system.
  • composition of these MCrAlY layers can vary, however, all MCrAlY layers are subject despite the overlying Ceramic layer of corrosion by oxidation, sulfidation, Nitridation or other chemical and / or mechanical Attacks.
  • the MCrAlY layer often degrades in a stronger one Dimensions as the metallic substrate, i. the life of the Composite system of substrate and layer is determined by the lifetime of the MCrAlY layer.
  • the MCrAlY interlayer is only after prolonged use conditionally functional, however, the substrate can still be fully functional.
  • the powder bed requires a lot of material and the crucible takes up a lot of space in the oven during the heat treatment.
  • the heat process also takes because of the large heat capacity longer.
  • EP-A-0 713 957 discloses a method for local Removal of corrosion products from turbine components. Of the Component is masked and aluminum is applied and into it diffused to create a sacrificial zone, which then removed along with the corrosion products.
  • the invention overcomes the disadvantages described a method as described in claim 1.
  • the method according to the invention has the advantage that layer regions, for example corrosion products of components, are removed in a simple manner.
  • layer regions for example corrosion products of components
  • the ablation can be achieved by mechanical methods, e.g. Sandblasting, Water jets, dry ice blasting, and / or by chemical processes, e.g. an acid treatment.
  • the detergent on the component at least partially liable, can in an advantageous manner, for example. Front and Rear side of the component at the same time according to the invention Procedure of corrosion products are removed.
  • the adhesion of the cleaning agent on the component can on advantageous manner done by the fact that the detergent has a paste-like consistency, for example the cleaning agent contains a binder.
  • the cleaning agent can also be mixed with a carrier liquid with or without binder and be brushed onto the component or the component is coated by immersion in a flowable mass of liquid and detergent with the cleaning agent.
  • the cleaning agent can also be advantageously applied only locally on the component, since areas that are not corroded need no application of the cleaning agent, which detergent can be saved.
  • the application of the cleaning agent is advantageously carried out near the corrosion products because it causes the at least one component of the cleaning agent has short diffusion paths during the heat treatment.
  • the cleaning agent is, for example, in a thin layer the component is applied so that in relation to the embedding of the Component consumed in a powder bed significantly less material becomes.
  • the crucible means Heat treatment, that in the oven no place through the voluminous crucible is consumed, so that more components in a furnace cycle can be accommodated, which the Reduced process costs.
  • an ablation process for example an acid treatment
  • the surface of the non-corroded component becomes uniform ablated.
  • the corrosion creates areas of the component and / or corrosion products resulting from the acid treatment not so easy to remove or remove, So they are more resistant to erosion. This leads to a Acid treatment as ablation process to an unwanted, uneven erosion on corroded or degraded Components.
  • the formation effected by the treatment according to the invention at least one victim zone in theBasedtragenden Layer area, i. the more erosion resistant areas of the component causes that by degradation areas that have become more resistant to abrasion than material of the non-degraded component can be removed or the any existing high erosion resistance of a not degrade degraded layer area.
  • the sacrificial zone advantageously has MCrAlY layers a metallic impregnating component, advantageously Aluminum, aluminum compound or an aluminum alloy on,
  • the cleaning agent may be advantageous to the metal component Way also included in the form of a metal complex. Consequently For example, the mixing of a metallic one is omitted Powder with a carrier substance or the activating agent.
  • the impregnating component must be removed from the cleaning agent at least partially diffuse into the component. This happens advantageously in that the impregnating component is applied in gaseous form to the component.
  • the gaseous Compound is formed by a reaction with the activating agent, wherein the impregnating agent advantageously does not melt, causing the process temperatures and thus process costs are reduced.
  • halogen compounds e.g. Ammonium chloride, which forms aluminum chloride with aluminum.
  • the formation of the gaseous compound can be controlled by advantageously adding a carrier substance, for example aluminum oxide, to the cleaning agent, whereby the gas formation is controlled and uniform.
  • a carrier substance for example aluminum oxide
  • the method is advantageously suitable for layer systems, such as a turbine blade, which have a layer system consisting of a metallic substrate, an MCrAlY layer and a ceramic thermal barrier coating applied thereto.
  • Corrosion products on the MCrAlY layer lead below the corrosion products (Al 2 O 3 ), to a depletion of aluminum in the MCrAlY layer, which thereby become more resistant to acid treatment.
  • the cleaning agent contains aluminum as a metallic component, however, aluminum according to the process of the invention re-accumulates in the previous aluminum-depleted areas of the MCrAlY layer, so that these areas, such as the MCrAlY layer, then dissolve by acid treatment on these areas located corrosion products are replaced with.
  • abrasion resistant layer areas or degraded areas e.g. Areas that Contain corrosion products that have a layer on the corroded component form, but also corrosion products, extending below the surface of the corroded component are located.
  • the area of detergent on the component near the surface is disposed of the component, depleted at the at least one Impregnation.
  • the heat treatment is over, if the victim zones are large enough, i. in case of MCrAlY layer sufficient on aluminum depleted areas again enriched with aluminum. If not already the case is, the detergent can be removed and the component can then undergo a thermal treatment be, wherein advantageously the impregnating component of the detergent already in the component through Diffusion is present, by diffusion deeper into the Part penetrates and so the victim zone or Sacrificial layer in an advantageous manner in depth increased.
  • An optimal temperature of the thermal treatment is above the temperature of the heat treatment to the solution annealing temperature of the component.
  • FIG. 1 shows a component 1 made of metal, a metal alloy or of a metal compound attached to a surface 7 outer corrosion products 4 and / or inside the component 1 internal corrosion products 5, the example in Separate areas are available.
  • the corrosion products 4 may also be contiguous, or be present on the entire surface 7, so one Form corrosion layer.
  • the component 1 may be solid or a layer or a region a composite or layer system 16 (Fig. 5, 6).
  • the Corrosion products 4, 5 have been found during the use of the Component 1 formed and are for further use of the Component 1 undesirable and must be removed. this happens often by a treatment in an acid bath.
  • the method according to the invention makes it possible to use the corrosion products completely and evenly with the material of the Component 1 to remove.
  • a coarse Removal of corrosion products or other areas by mechanical methods e.g. Sandblasting, and / or chemical Means, e.g. Acid bath, done.
  • the ablated layer region 52 is through a Dashed line marked and includes all Corrosion products 4, 5.
  • the cleaning agent 10 contains at least one impregnating component 13, which in a heat treatment with at least one Activation component of the cleaning agent 10 to at least a gaseous compound reacts.
  • the gaseous compound becomes the impregnating component 13 is brought into contact with the component 1 or beats There down and forms there in the material of the component. 1 for example, an impregnation layer. From this impregnation layer or directly from the gaseous compound diffuses the Impregnating agent in the areas with the corrosion products 4, 5 a. The impregnation component 13 is then at least partly in the areas with the corrosion products 4, 5 available.
  • a layer region 52 to be removed is indicated by a dashed line.
  • the Layer region 52 to be removed comprises all Corrosion products, but can also be deeper than the deepest Corrosion product 5 be present.
  • the acid treatment reduces a thickness of the component 1, of a thickness d (FIG. 3) to a smaller thickness d '( Figure 4).
  • FIG. 4 shows a component 1 without internal and external corrosion products 4, 5 due to the treatment according to the invention Method.
  • the choice of the material of the at least one impregnating component depends on the composition of the material of the component 1 and / or the corrosion products 4, 5 from.
  • the activation component has the task of the impregnating component to bring to the surface 7 of the part. This happens because the activation component with the Impregnating component can form a gaseous compound, which can be deposited on the surface 7 of the component 1. To this end, e.g. Halogen compounds into consideration.
  • FIG. 5 shows as a component 1 a layer system 16 which for example, by a turbine blade or vane is formed.
  • the layer system 16 consists in this case of a Sub-3strat 19, for example a superalloy, for example.
  • the base composition Ni 3 Al.
  • a layer 22 is applied, for example of the composition MCrAlY, where M stands for a chemical element Cr, Ni or Fe.
  • This so-called MCrAlY layer forms a corrosion protection layer, which can also act as an adhesion-promoting layer for a ceramic thermal insulation layer (not shown) applied to the layer 22.
  • the layer system 16 it comes, for example. for oxidation, nitridation or sulfidation, i. degradation the MCrAlY layer 22, so that in the layer 22 Form areas with corrosion products 4, 5 (not shown).
  • the corrosion products 4, 5 form an at least partially existing layer in or on or below the surface 7 of the component 16.
  • the layer region 52 to be removed is indicated by a dashed line and includes all Corrosion products 4, 5 or the entire layer 22.
  • the MCrAlY layer can also deplete of chromium (Cr), so that the impregnating component 13, for example the elements Al and / or Cr having.
  • Cr chromium
  • Impregnating component 13 may also include other metals, e.g. Cobalt, or elements or combinations thereof. Both the corrosion products 4 and the sacrificial zone 25 have in the acid bath opposite the material of the layer 22, So the MCrAlY, a higher acid resistance.
  • a rough removal the ceramic thermal barrier coating, the corrosion products or from other areas by mechanical methods, e.g. Sandblasting, and / or chemical agents, e.g. acid bath respectively.
  • the metal component 13 which in this example is aluminum contains, both in the areas with the corrosion products 4 as well as in the victim zones 25, so that there at least a metal component 13 is present. Only through the enrichment with the metal component 13 may be in an acid bath treatment of the layer system 16 a certain layer thickness Layer 22 (MCrAlY) are removed evenly.
  • MrAlY layer thickness Layer 22
  • the cleaning agent 10 may also include several metallic components 13 (Al, Cr), if that for the composition the corrosion products or the depleted victim zones 25 is required.
  • the metallic component 13 is, for example, with at least one Carrier substance, for example aluminum oxide or aluminum silicate, mixed.
  • the cleaning agent 10 may be metallic Component 13 also in the form of a metal complex.
  • the cleaning agent 10 has at least one activating agent, for example a halogen compound, for example in the form of ammonium chloride (NH 4 Cl).
  • a halogen compound for example in the form of ammonium chloride (NH 4 Cl).
  • the aluminum reacts as metal component 13 with the halogen compound to a gaseous compound.
  • a gaseous compound This is in Example of ammonium chloride aluminum chloride.
  • the gaseous Connection penetrates into the at least one victim zone 25 or makes it possible to diffuse the aluminum into the component 1, by, for example, forming an impregnating layer (FIG. 6). Therefore, the metal component 13 does not need to be melted become. But it can also be that the gaseous Compound forms only at temperatures above the Melting point of the at least one impregnating component is because, for example, a sublimation occurs.
  • the impregnating component 13 and the activating component are contained in a compound (eg AlF 3 ).
  • the heat treatment forms a gaseous compound aluminum fluoride (AlF).
  • the heat treatment can be carried out in vacuum or inert gases Hydrogen and / or argon are performed.
  • the cleaning agent 10 may, in addition to the metal component 13, the carrier substance and the activating agent one more for example, organic binders (carboxyl methacrylate, carboxyl methyl cellulose or similar compounds), so that the detergent 10 is a pasty or muddy Has consistency, so the corroded component Apply 1 well and due to the binder on the component 1, 16 can adhere.
  • organic binders carboxyl methacrylate, carboxyl methyl cellulose or similar compounds
  • the invention is not limited to the said application methods.
  • the concentration is reduced the metal component 13 in the surface 7 facing Range of detergent 10. From this range can only still slightly a metal component 13 or in extreme cases no metal component 13 more diffuse into the component 1. Another, desired deeper penetration of the Metal component 13 in the depth of the material 1 is only by further diffusion of the already diffused Metal component 13 instead. However, a longer hold would be of the component 1 at elevated temperature cause from a surface 11 of the cleaning agent 10 the Metal component 13 via the gaseous compound to Surface regions 8 of the component 1 passes, on which no Detergent 10 was applied and also no penetration the metallic component 13 or the reaction products is desired.
  • the cleaning agent 10 in this case after a certain duration of the heat treatment removed and finds it just another, desired penetration of the Metal component 13 in the depth of the material 1 by Diffusion of already diffused into the component 1 metallic component 13 due to a thermal treatment of the component 1 without detergent 10 instead.
  • the Thermal treatment is, for example, by a solution annealing of Component 1 allows.
  • the removal of the cleaning agent 1 poses no problems because the metallic component 13 is not melted is.
  • the cleaning agent 10 may be local, in particular via the erosion resistant Areas, large or full the component 1, 16 may be applied.
  • Layer material MCrAlY
  • Depth of corrosion products in the layer 150 ⁇ m (depleted Al area)
  • Application of the cleaning agent 10 results in a sacrificial zone 25 to a depth of 80 microns with a heat treatment at 925 ° C and 2h duration, After removal of the cleaning agent, a thermal treatment takes place at 1120 ° C for a maximum of 20 hours: Sacrificial zone 25 has a depth of 150 ⁇ m.
  • the duration of the thermal treatment or the temperature can be based on of calibration curves (diffusion depth depending on time and temperature) of the spatial extent of the corrosion products be adapted in the component.
  • the cleaning agent 10 may before the Heating a mask layer are applied, which prevents that of the surface 11 of the cleaning agent 10 the metallic component 13 reaches surfaces 8 of the component 1, on which no detergent was applied and also no penetration of the metallic component 13 is desired is.
  • the cleaning agent 10 remain on the component 1 and still carried out a heat treatment to achieve the effect described above.
  • the invention is not limited to parts of gas turbines, but also works for components that have at least one Layer, for example.
  • the invention is not limited to components that have no layers, but their corrosion products removed must be such. in reaction vessels in the chemical industry.
  • FIG. 7 shows a layer system 16 that consists of a substrate 19, for example a nickel-based superalloy, an intermediate layer, in particular an MCrAlY layer 28, and an outer heat-insulating layer 31.
  • the layer system 16 was exposed in use mechanical and thermal loads and should be restored for re-use (refurbishment).
  • the thermal barrier coating 31 is removed by sandblasting, for example. This can be done in a simple manner by mechanical means, since the heat-insulating layers 31 are mostly ceramic, ie brittle layers.
  • the at least one intermediate layer 28 is metallic and is more difficult to remove by mechanical means.
  • FIG. 8 shows the layer system 16 in which the thermal barrier coating 31 has already been removed and the intermediate layer 28 is shown enlarged.
  • the intermediate layer 28 is degraded. Degradation means in the case that corrosion products, ie oxides, nitrides and sulfides have formed or that a phase segregation has taken place, for example the coagulation of aluminum phases 43 or a change in the concentration structure due to diffusion.
  • the intermediate layer 28 does not necessarily have the following appearance: In a first zone 34, on which the thermal barrier coating 31 was applied, there are external 4 and internal corrosion products 5 which have been formed by contact and reaction with a reactive medium.
  • a second zone 37 extending towards the substrate 19 connects to the first zone 34, for example, are none Corrosive products present, but through thermal Stress related diffusion has become aluminum or Aluminum phases or other elements coagulated.
  • the second zone 37 is followed by a third zone 40, located between the substrate 19 and the second zone 37 located.
  • the concentration has the intermediate layer 28 starting from their Initial composition due to diffusion of elements changed into the substrate 19.
  • This is in the case of a MCrAlY interlayer 28 and a Ni-A1 superalloy as Substrate 19, for example, aluminum, in the MCrAlY layer in higher concentration than in the substrate 19 exists and therefore due to the Concentration difference in the substrate diffuses. So is, for example, the entire intermediate layer 28 degrades the layer 52 to be removed represents.
  • the third zone 40 can also be that only the first zone and the second zone 34, 37 are degraded and the third zone 40 shows no signs of degradation. Nevertheless, can also the third zone 40 by impregnation with the Impregnating 13 made part of a sacrificial zone 25 and be removed.
  • FIG. 10 shows a substrate 19, for example a nickel-base superalloy a turbine blade through the Use in a degraded near-surface region 46 which degrades the layer region 52 to be removed represents.
  • the degraded area 46 is for example by corrosion or by in-diffusion of elements in the substrate 19 or path diffusion of elements of the Substrate 19 in layers or layers resting thereon Layer regions of the substrate emerged.
  • Impregnating 13 in the degraded area 46th introduced so that the degraded region 46 to a Sacrificial zone 25 will and remove itself completely and easily leaves (Figure 11).
  • the layer region 52 to be removed comprises but at least the degraded area can also be increased become.
  • FIG. 12 shows a layer system 16 that consists of a substrate 19 and a, for example, undegraded chromium layer 49, which represents the layer region 52 to be removed, since a chromium-containing or chromium layer 49 has a high resistance to erosion against chemical erosion processes.
  • a chromium-containing or chromium layer 49 has a high resistance to erosion against chemical erosion processes.
  • the application example is not limited to a chromium layer or the chromium layer can also be degraded by corrosion, for example.
  • the layer 49 can be badly removed with the usual removal methods such as acid stripping.
  • Impregnating 13 penetrate into the layer 49, whereby the layer 49 with the usual methods, For example, it is easier to remove acid stripping (Figure 13) because the resistance to erosion has been reduced.
  • the impregnating component 13 in the Substrate penetrate or increases the victim zone 25th through an extension zone 54 during the thermal treatment due to diffusion.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Engineering & Computer Science (AREA)
  • General Chemical & Material Sciences (AREA)
  • ing And Chemical Polishing (AREA)
  • Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé pour enlever une zone de couche d'un composant en métal ou en alliage métallique. Selon la technique actuelle, les produits de corrosion d'un composant sont enlevés, lors d'une première opération, par application d'une masse fondue ou par réchauffement dans un lit de poudre volumineux, ce qui nécessite des températures élevées ou un grand espace. Le procédé selon l'invention pour enlever des produits de corrosion d'un composant (1) consiste à appliquer localement un agent de nettoyage (10) qui, au moyen d'un produit réactionnel gazeux, élimine les produits de corrosion.

Claims (27)

  1. Procédé pour enlever au moins une zone (52) de couche d'un élément (1) en métal et/ou en au moins un composé métallique
       qui comprend les stades suivants :
    on dépose localement un agent (10) de nettoyage à plusieurs constituants sur une surface de l'élément (1) corrodé, l'agent (10) de nettoyage comprenant au moins un constituant (13) d'imprégnation qui peut diffuser dans la zone (52) de couche de l'élément (1) et/ou en au moins un constituant d'activation,
    on traite thermiquement l'élément (1) par l'agent (10) de nettoyage de façon
    à ce que le au moins un constituant (13) d'imprégnation et le au moins un constituant d'activation forment au moins un composé gazeux,
    on forme au moins une zone (25) sacrificielle au moins en partie dans la zone (52) de couche à enlever de l'élément (1) en raison du traitement thermique en faisant venir le au moins un composé gazeux en contact avec l'élément (1) de sorte que la résistance à l'enlèvement des zones jusqu'ici plus résistantes à l'enlèvement ait au moins diminué,
    on enlève la couche (52) à enlever avec la au moins une zone (25) sacrificielle.
  2. Procédé suivant la revendication 1,
    caractérisé en ce que l'agent (10) de nettoyage adhère au moins en partie à l'élément (1).
  3. Procédé suivant la revendication 1,
    caractérisé en ce que l'on forme la au moins une zone (25) sacrificielle au moins en partie par des zones de l'élément (1) qui présentent le au moins un constituant (13) d'imprégnation.
  4. Procédé suivant la revendication 1,
    caractérisé en ce que l'agent (10) de nettoyage a comme au moins un constituant (13) d'imprégnation au moins un constituant (13) métallique ou un constituant (13) contenant du métal.
  5. Procédé suivant la revendication 1,
    caractérisé en ce que le au moins un constituant (13) d'imprégnation pénètre directement de la phase gazeuse ou après dépôt sur l'élément (1) par diffusion dans l'élément (1).
  6. Procédé suivant la revendication 1,
    caractérisé en ce que la température lors du traitement thermique de l'élément (1) par l'agent (10) de nettoyage est inférieure au point de fusion le plus bas du au moins un constituant (13) d'imprégnation.
  7. Procédé suivant la revendication 1,
    caractérisé en ce que l'agent (10) de nettoyage contient comme au moins un constituant d'activation un composé halogéné.
  8. Procédé suivant la revendication 4,
    caractérisé en ce que le constituant (13) métallique est en aluminium ou le constituant (13) contenant du métal contient de l'aluminium.
  9. Procédé suivant la revendication 1 ou 3,
    caractérisé en ce que la au moins une zone (25) sacrificielle comporte au moins en partie de l'aluminium ou des composés d'aluminium.
  10. Procédé suivant une ou plusieurs des revendications 1, 2, 4 ou 7,
    caractérisé en ce que l'agent (10) de nettoyage comporte comme autre constituant au moins une substance support.
  11. Procédé suivant la revendication 10,
    caractérisé en ce que la substance support est de l'oxyde d'aluminium.
  12. Procédé suivant la revendication 1 ou 2,
    caractérisé en ce que l'agent (10) de nettoyage a une consistance pâteuse.
  13. Procédé suivant la revendication 1, 2 ou 12,
    caractérisé en ce que l'agent (10) de nettoyage a comme autre constituant au moins un liant pour donner la consistance pâteuse de l'agent (10) de nettoyage.
  14. Procédé suivant la revendication 1 ou 2,
    caractérisé en ce que l'élément (1) est un système (16) à couches ayant au moins une couche (22), notamment une aube de turbine revêtue,
    la zone (52) de couche à enlever correspondant à la couche (22).
  15. Procédé suivant la revendication 4,
    caractérisé en ce que la couche (22) est une couche en MCrAIY.
  16. Procédé suivant la revendication 1, 2 ou 15,
    caractérisé en ce que l'on enlève les produits (4) de corrosion extérieurs à la surface (7) de l'élément (1, 16).
  17. Procédé suivant la revendication 1, 2 ou 15,
    caractérisé en ce que l'on enlève les produits (4) de corrosion intérieurs à la surface (7) de l'élément (1, 16).
  18. Procédé suivant la revendication 1 ou 2,
    caractérisé en ce que l'on enlève dans un stade intermédiaire l'agent (10) de nettoyage après le traitement thermique.
  19. Procédé suivant la revendication 18,
    caractérisé en ce que l'on augmente dans un stade intermédiaire la au moins une zone (25) sacrificielle dans la profondeur de l'élément (1) par un thermotraitement.
  20. Procédé suivant la revendication 19,
    caractérisé en ce que la température du thermotraitement est au moins en partie supérieure à la température du traitement thermique.
  21. Procédé suivant la revendication 4 ou 20,
    caractérisé en ce que la température du thermotraitement permet d'avoir un recuit de mise en solution de l'élément (1).
  22. Procédé suivant la revendication 1,
    caractérisé en ce que l'on dépose l'agent (10) de nettoyage à la surface (7) de l'élément (1) dans la zone de produit (4, 5) de corrosion.
  23. Procédé suivant la revendication 1, 5 ou 6,
    caractérisé en ce que le composé gazeux produit une couche d'imprégnation dans l'élément (1) qui est constituée au moins en partie du au moins un constituant (13) d'imprégnation.
  24. Procédé suivant la revendication 1,
    caractérisé en ce que la zone (52) de couche contient des produits (4, 5) de corrosion.
  25. Procédé suivant la revendication 1,
    caractérisé en ce que la zone (52) de couche est altérée au moins en partie.
  26. Procédé suivant la revendication 1,
    caractérisé en ce que la zone (52) de couche est altérée au moins en partie par diffusion d'éléments chimiques hors de la zone (52) de couche ou dans celle-ci.
  27. Procédé suivant la revendication 1,
    caractérisé en ce que la zone (52) de couche est une couche de chrome ou une couche contenant du chrome.
EP02730264A 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique Expired - Lifetime EP1432847B8 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02730264A EP1432847B8 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP01123593A EP1298230A1 (fr) 2001-10-01 2001-10-01 Procédé pour enlever des produits de corrosion d'un composant métallique
EP01123593 2001-10-01
EP02730264A EP1432847B8 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique
PCT/EP2002/005490 WO2003029521A1 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique

Publications (3)

Publication Number Publication Date
EP1432847A1 EP1432847A1 (fr) 2004-06-30
EP1432847B1 true EP1432847B1 (fr) 2005-03-09
EP1432847B8 EP1432847B8 (fr) 2005-06-29

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EP01123593A Withdrawn EP1298230A1 (fr) 2001-10-01 2001-10-01 Procédé pour enlever des produits de corrosion d'un composant métallique
EP02730264A Expired - Lifetime EP1432847B8 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP01123593A Withdrawn EP1298230A1 (fr) 2001-10-01 2001-10-01 Procédé pour enlever des produits de corrosion d'un composant métallique

Country Status (6)

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US (2) US7138065B2 (fr)
EP (2) EP1298230A1 (fr)
JP (1) JP2005504179A (fr)
CN (1) CN1328413C (fr)
DE (1) DE50202441D1 (fr)
WO (1) WO2003029521A1 (fr)

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* Cited by examiner, † Cited by third party
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EP1298230A1 (fr) * 2001-10-01 2003-04-02 Siemens Aktiengesellschaft Procédé pour enlever des produits de corrosion d'un composant métallique
EP1367144A1 (fr) * 2002-05-29 2003-12-03 Siemens Aktiengesellschaft Procédé d'enlèvement des parties d'un composant métallique
EP1676938A1 (fr) * 2004-12-30 2006-07-05 Siemens Aktiengesellschaft Methode de fabrication d'un component d'une turbine et le component d'une turbine
EP1870485A1 (fr) * 2006-06-22 2007-12-26 Siemens Aktiengesellschaft Composition et méthode de métallisation d'un composant
EP1870497A1 (fr) * 2006-06-23 2007-12-26 Siemens Aktiengesellschaft Procédé d'enlèvement électrochimique d'un revêtement métallique d'un substrat
EP1890004A1 (fr) 2006-08-08 2008-02-20 Siemens Aktiengesellschaft Procédé pour la production d'un revêtement à partir du matériau d'un revêtement recyclé
DE102006044416A1 (de) * 2006-09-18 2008-03-27 Siemens Ag Verfahren zum elektrochemischen Be- oder Entschichten von Bauteilen
DE102008004559B4 (de) * 2007-01-23 2017-03-16 General Electric Technology Gmbh Verfahren zum Bearbeiten eines thermisch belasteten Bauteils
WO2009036776A1 (fr) 2007-09-13 2009-03-26 Siemens Aktiengesellschaft Produit sidérurgique résistant à la corrosion pour récipients sous pression, procédé pour sa fabrication, et élément de turbine à gaz
DE102013111854A1 (de) * 2013-10-28 2015-05-21 Aixtron Se Verfahren zum Entfernen von Ablagerungen an den Wänden einer Prozesskammer
CN106757044B (zh) * 2016-12-21 2018-12-14 中国南方航空工业(集团)有限公司 一种空心叶片内腔低熔点合金清理方法
PL429832A1 (pl) * 2019-05-05 2020-11-16 Żrodowski Łukasz Sposób wytwarzania addytywnego trójwymiarowych obiektów
WO2022005696A1 (fr) * 2020-07-03 2022-01-06 Applied Materials, Inc. Procédés de remise à neuf de composants aérospatiaux
CN115595581B (zh) * 2022-11-10 2024-04-26 上海电气燃气轮机有限公司 一种服役后热部件粘接层的去除方法

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Also Published As

Publication number Publication date
JP2005504179A (ja) 2005-02-10
EP1432847A1 (fr) 2004-06-30
US7138065B2 (en) 2006-11-21
US20040244817A1 (en) 2004-12-09
WO2003029521A1 (fr) 2003-04-10
CN1549874A (zh) 2004-11-24
US20070023392A1 (en) 2007-02-01
DE50202441D1 (de) 2005-04-14
EP1432847B8 (fr) 2005-06-29
CN1328413C (zh) 2007-07-25
EP1298230A1 (fr) 2003-04-02
US7429337B2 (en) 2008-09-30

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