EP2537959B1 - Revêtement multicouches anti-usure et procédé de fabrication - Google Patents

Revêtement multicouches anti-usure et procédé de fabrication Download PDF

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Publication number
EP2537959B1
EP2537959B1 EP20110170936 EP11170936A EP2537959B1 EP 2537959 B1 EP2537959 B1 EP 2537959B1 EP 20110170936 EP20110170936 EP 20110170936 EP 11170936 A EP11170936 A EP 11170936A EP 2537959 B1 EP2537959 B1 EP 2537959B1
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Prior art keywords
layer
hardness
multilayer film
high level
component
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German (de)
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EP2537959A1 (fr
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Thomas Dr. Uihlein
Wolfgang Eichmann
Falko Dr. Heutling
Stefan Schneiderbanger
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MTU Aero Engines AG
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MTU Aero Engines AG
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/324—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal matrix material layer comprising a mixture of at least two metals or metal phases or a metal-matrix material with hard embedded particles, e.g. WC-Me
    • 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
    • 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
    • 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
    • C23C28/347—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 layers adapted for cutting tools or wear applications
    • 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
    • C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
    • C23C28/42—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by the composition of the alternating layers
    • 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
    • C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
    • C23C28/44—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by a measurable physical property of the alternating layer or system, e.g. thickness, density, hardness

Definitions

  • the present invention relates to a coating for components of a gas turbine or an aircraft engine with a multi-layer of several layers of different hardness and a method for producing such a coating and thus equipped components of a gas turbine or an aircraft engine, in particular vanes and blades.
  • Similar wear protection layers are also used in the US 2007/0099027 A1 described. These have a layer stack of different nitrides, such as titanium nitride and Zitkonnitrid or corresponding borides and carbides and an underlying hard layer on.
  • hot gas corrosion protection layers are known, as for example in the DE 10 2005 060 243 A1 or the EP 0 587 341 A1 are described. Another example is in the WO 2010/138096 given. These oxidation protection layers are based essentially on MCrAlY coatings in which M is formed by iron, cobalt or nickel. In this case, it is particularly important to have a corresponding chromium content of the coating, which can be increased by enriching the chromium content. The chromium content ensures that a slowly growing, dense chromium oxide layer is formed, which prevents further oxidation. However, such layers are not suitable for use in areas with high wear or erosion stress.
  • the US 6,503,340 B1 describes a coating for increasing erosion and high temperature resistance with an outer nitride or carbide layer and an underlying chromium carbide coating.
  • the WO 2008/140479 A2 describes a thermal barrier coating system that is insensitive to mechanical impact.
  • two different types of anti-wear or anti-erosion layers are combined to achieve, through the combination, an improvement in property profile in terms of wear resistance as well as hot gas corrosion resistance.
  • the coating comprises a layer of high hardness as well as a multi-layer with several partial layers of different hardness.
  • the information on the hardness here are initially relative to see and on the one hand in relation to the base material of the component to be coated as well as within the layers or sub-layers in the coating.
  • the layer of high hardness which, for example, lies in the range of a hardness of .gtoreq.20 HRC, in particular .gtoreq.40 HRC and above.
  • the hardness of the high hardness layer may be equal to or higher than these values for many applications.
  • the hardness to be adjusted can be adapted to this base material, so that even lower hardness values are possible in individual cases. The same applies to the multi-layer system and the sublayers located therein.
  • first partial wear protection system with a layer of high hardness and a second partial wear protection system with a multi-layer
  • the coating according to the invention for all angles of incidence of impinging particles provides protection, since the multi-layer for small angles of incidence in the range of 0 ° to 30 ° has good properties, while the layer of high hardness is most effective at large angles of incidence of 60 ° to 90 °.
  • the multi-layer layer may comprise a plurality of hard and soft sub-layers, which are arranged alternately, so that a soft and a hard sub-layer are on top of each other and this sequence is repeated several times.
  • Such wear layers are known by themselves from the prior art (see above) and therefore require no further explanation.
  • the soft layers can be realized for example by soft metallic sublayers or soft ceramic sublayers, while the hard sublayers are usually produced by ceramic sublayers.
  • the thickness of a single partial layer of the multi-layer layer which in turn may itself consist of several partial layers, can be in the range of a few nanometers up to 20 micrometers, preferably up to 10 micrometers.
  • the hard sublayers may be formed by nitrides or nitrogen rich layers of chromium, aluminum and / or titanium.
  • the soft sub-layers may be formed on the basis of iron, cobalt, nickel, titanium, chromium or aluminum alloys or corresponding ceramic materials, such as CrN.
  • the multi-layer layer is deposited by PVD (physical vapor deposition) deposition, while the high-hardness layer is applied between the multi-layer and the component to be coated by means of a high-speed spraying method, such as thermal spraying or cold gas spraying.
  • PVD physical vapor deposition
  • the high hardness layer is formed by a metal alloy layer which has high hardness by means of dispersion hardening, precipitation hardening or solid solution strengthening, but at the same time has a certain ductility and in particular avoids the negative mechanical properties of materials hardened with high carbide contents.
  • alloys based on cobalt such as CoMoCrSi alloys or CoCrWSi alloys, such as, for example, are suitable for use here.
  • MCrAlY alloys can also be provided with dispersion particles of oxides, nitrides and / or borides, where M is iron, cobalt or nickel.
  • These layers not only provide sufficient hardness, but can also have a corresponding chromium content to improve the hot gas corrosion resistance to form a slowly growing and dense chromium oxide layer, in particular chromium contents of ⁇ 18 wt .-%, preferably ⁇ 20 wt .-%.
  • chromium contents ⁇ 18 wt .-%, preferably ⁇ 20 wt .-%.
  • carbide content can be limited to the range of unavoidable impurities by avoiding carbon contents or suitable composition of the other alloy constituents.
  • a chromium-rich layer is produced by chromium plating, that is, by diffusing chrome.
  • the chromium content in the chromium-rich layer may be up to 30% by volume, preferably up to 20% by volume.
  • chromium plating can be applied to coatings on steel components.
  • the high-hardness sprayed layer can be smoothed by polishing or grinding or other suitable methods, such that a high-quality PVD coating is obtained, especially in a subsequent direct application of the PVD multilayer coating results.
  • a porous layer may be formed between the component to be coated and the high-hardness layer to provide a layer in the formation of micro-cracks in outer layers of the protection system which prevents crack growth due to crack-tip broadening in the pores.
  • the porous layer can be produced in particular by cold gas spraying.
  • the thickness of the high-hardness layer may be selected to be up to 150 microns, more preferably up to 100 microns, while the high-chromium layer may have a thickness of up to 20 microns, preferably up to 10 microns.
  • a corresponding, coated component of a gas turbine or an aircraft engine can only be partially coated and, in particular in certain areas where certain requirements are not met, can only be provided with one of the partial layer systems, for example with the layer of high hardness, with the layer of high hardness including a chromium-rich layer or merely with a multilayer or other combinations of the individual sub-layers of the presented coating system.
  • the component to be coated may in particular be components based on iron, nickel or titanium materials.
  • the Fig. 1 shows a partial cross-section through a coating according to a comparative example on a component 1.
  • the coating comprises a layer 2 of high hardness and a multi-layer coating 3. Both the layer 2 high hardness and the multi-layer 3 are already a wear protection coating, but wherein the structure of the individual partial wear protection coating and their mode of action are different. However, a balanced property profile of the entire wear-resistant coating can be achieved by combining the different partial wear-protection coatings.
  • the layer 2 of high hardness, ie the first part wear protection coating is realized by a hard alloy or by another metal layer with high hardness, which is achieved for example by dispersion hardening, precipitation hardening or solid solution hardening.
  • ceramic particles can be incorporated into the alloy such as oxides, nitrides, borides, for example alumina.
  • corresponding materials which can be used for the high hardness layer 2 are cobalt base alloys such as CoMoCrSi or CoCrWSi alloys marketed under the trade names Tribaloy and Stellite.
  • MCrAlY alloys with M equal to iron, cobalt or nickel can be used, which can be provided in particular with dispersion particles, such as alumina, to increase the hardness.
  • the layer 2 of high hardness is applied by means of high-speed spraying processes, such as thermal spraying, also known as high-velocity oxide-fuel (HVOF) spraying or flame spraying.
  • high-speed spraying processes such as thermal spraying, also known as high-velocity oxide-fuel (HVOF) spraying or flame spraying.
  • the high hardness layer 2 After application of the high-hardness layer by cold gas spraying or flame spraying, the high hardness layer 2 can be smoothed if necessary, for example by appropriate grinding and polishing.
  • the multi-layer layer is applied in layers by means of vapor deposition (Physical Vapor Deposition PVD).
  • the multilayer 3 comprises a sequence of soft and hard sub-layers 4, 5, 6, 7, soft sub-layers 4, 6 alternating with hard sub-layers 5, 7.
  • the outer layer is preferably formed by a hard part-layer 7.
  • the hard sub-layers 5, 7 may be formed by ceramic materials, in particular nitrides or nitrogen-rich layers of aluminum, titanium or chromium with additions of yttrium or carbon. In addition, however, other ceramic materials are conceivable, especially on an oxide basis.
  • the soft sub-layers 4, 6 may also be formed of ceramic materials with the same chemical elements, with a higher proportion of the metallic elements, for example, a lower hardness is adjustable.
  • the soft sub-layers 4, 6 may be formed by metallic layers based on iron, cobalt, nickel, titanium, chromium or aluminum or combinations thereof.
  • An example of a layer sequence could be given for example by the formation of the soft sub-layers 4, 6 as CrN layers and the hard sub-layers as CrAIN layers.
  • the soft sub-layers 4, 6 and / or the hard sub-layers 5, 7 can in turn themselves be composed of several layers.
  • the layer thickness of the partial layers 4 to 7 of the multi-layer layer 3 can be selected in the range of a few nanometers to a few micrometers.
  • the layer 2 of high hardness can also be deposited with a layer thickness of about 100 microns.
  • the Fig. 2 shows a first embodiment of a coating according to the invention, in which the identical components except for the coated component with the same reference numerals, only increased by 10, are provided.
  • a layer 12 of high hardness and a multi-layer 13 with the partial layers 14 to 17 are again provided on the component 10.
  • the layer of high hardness 12 and the multi-layer 13 are constructed in the same manner as in the embodiment of Fig. 1 so that an additional description is unnecessary.
  • a chromium-rich layer 11 formed by chromating the high-hardness layer 12.
  • the chromium-rich layer 11 may be formed as a diffusion layer formed in the previously deposited high hardness layer 12 by diffusing the chromium.
  • the chromium content may in particular be up to 30% by volume, preferably up to 20% by volume, of chromium.
  • the chromium-rich layer enhances high-temperature corrosion resistance because the chromium forms a dense, thin chromium oxide layer that prevents further hot gas corrosion.
  • the Fig. 3 shows in a further embodiment, a coating according to the invention on a component 100, which for the most part of the coating from the Fig. 2 equivalent. Accordingly, again with the exception of the name of the component, the reference numerals for the Components chosen so that these compared to the embodiment of Fig. 1 only increased by 100.
  • Fig. 3 That's how it shows Fig. 3 a coating having a high hardness layer 102 followed by a chromium rich layer 111 and a multilayer 103 having sublayers 104 to 107.
  • the high hardness layer 102 and the multi-layer layer 103 correspond to the layers 12 and 2, and 13 and 3, respectively, of the previously described embodiments and need no further explanation.
  • the chromium-rich layer 111 corresponds to the chromium-rich layer 11 and is therefore also known.
  • an additional porous layer 101 is provided between the high hardness layer 102 and the component 100. This layer can be applied for example by cold gas spraying.
  • the porous layer 101 is effected by the defined introduction of porosity that any resulting microcracks from the outer layers of the protection system in crack growth can not penetrate into the base material of the component 100, but are prevented in the pores due to the dulling of the crack tip on the further crack growth .
  • the composition of the porous layer 101 is preferably selected to be similar to that of the base material of the component 100.
  • the components 1, 10, 100 can be formed in particular by iron, nickel or titanium-based alloys, the designation base alloy indicating here that the component with the largest proportion is formed by iron, nickel or titanium.

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  • Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Coating By Spraying Or Casting (AREA)

Claims (15)

  1. Revêtement pour des pièces d'une turbine à gaz ou d'un moteur d'avion avec une couche multiple (3, 13, 103) constituée de plusieurs couches partielles (4, 5, 6, 7 ; 14, 15, 16, 17; 104, 105, 106, 107) de duretés différentes, dans lequel la couche multiple (3, 13, 103) comprend une série répétée de couches partielles dures et souples (4, 5, 6, 7 ; 14, 15, 16, 17 ; 104, 105, 106, 107), dans lequel en particulier la couche partielle la plus extérieure est une couche dure, dans lequel sous la couche multiple entre la pièce et la couche multiple est disposée une couche (2, 12, 102) de dureté supérieure présentant une composition qui se distingue de la composition des couches partielles de la couche multiple, dans lequel la couche de dureté supérieure présente une dureté supérieure à celle de la pièce à revêtir et est un alliage de CoMoCrSi, un alliage de CoCrWSi ou un alliage de MCrAlY comprenant des particules dispersées d'oxydes, de nitrures et/ou de borures, où M est Fe, Co ou Ni,
    caractérisé en ce que
    entre la couche (2, 12, 102) de dureté supérieure et la couche multiple est disposée une couche (11, 111) comportant une proportion de chrome élevée.
  2. Revêtement selon la revendication 1,
    caractérisé en ce que
    le couche multiple (3, 13, 103) présente une série répétée d'une couche partielle métallique souple et d'une couche partielle, de céramique dure ou d'une couche partielle de céramique souple et d'une couche partielle métallique dure, dans lequel en particulier l'épaisseur des couches partielles de la couche multiple se situe dans une plage de quelques nm à 20 µm, de préférence est de 10 µm.
  3. Revêtement selon l'une des revendications précédentes,
    caractérisé en ce que
    les couches partielles dures de la couche multiple comprennent des nitrures ou des couches riches en azote avec du chrome, de l'aluminium et/ou du titane alors que les couches partielles souples de la couche multiple sont formées par des couches à base de Fe, Co, Ni, Ti, Cr, Al et leurs combinaisons.
  4. Revêtement selon l'une des revendications précédentes,
    caractérisé en ce que
    la couche (2, 12, 102) de de dureté supérieure est formée par une couche d'alliage métallique, qui présente une dureté élevée au moyen d'un durcissement par dispersion, d'un durcissement par dépôt ou d'une solidification de cristaux mixtes.
  5. Revêtement selon l'une des revendications précédentes,
    caractérisé en ce que
    la couche de dureté supérieure présente une proportion élevée de Cr en particulier ≥ 18 % en poids, de préférence ≥ 20 % en poids, en particulier avec en même temps une faible proportion de carbure de Cr de < 5 % en volume, en particulier < 1 % en volume, qui garantit qu'une couche protectrice d'oxyde de chrome est formée.
  6. Revêtement selon l'une des revendications précédentes,
    caractérisé en ce que
    dans la couche (11, 111) à proportion élevée de chrome, entre la couche (2, 12, 102) de dureté supérieure et la couche multiple, la proportion de chrome va jusqu'à 30 % en volume, de préférence jusqu'à 20 % en volume.
  7. Revêtement selon l'une des revendications précédentes,
    caractérisé en ce que
    sous la couche (2, 12, 102) de dureté supérieure est formée une couche poreuse (101) entre la couche de dureté supérieure et la pièce.
  8. Revêtement selon l'une des revendications précédentes,
    caractérise en ce que
    une couche de dureté supérieure présente une épaisseur allant jusqu'à 150 µm, en particulier jusqu'à 100 µm.
  9. Revêtement selon la revendication 6,
    caractérisé en ce que
    la couche à proportion élevée de chrome présente une épaisseur allant jusqu'à 20 µm, de préférence jusqu'à 10 µm.
  10. Pièce pour une turbine à gaz ou un moteur d'avion, en particulier une aube directrice ou une aube mobile comportant un revêtement selon l'une des revendications 1 à 9.
  11. Pièce selon la revendication 10,
    caractérisée en ce que
    la couche à proportion élevée de chrome (11, 111) et/ou la couche multiple (3, 13, 103) sont déposées sur la pièce (1, 10, 100) réparties uniquement dans des zones partielles.
  12. Pièce selon la revendication 10 ou 11,
    caractérisée en ce que
    la pièce (1, 10, 100) est formée d'un matériau à base de Fe, Ni ou Ti.
  13. Procédé de production d'un revêtement pour une pièce d'une turbine à gaz ou d'un moteur d'avion, en particulier selon l'une des revendications 1 à 10, dans lequel une couche (2, 12, 102) de dureté supérieure est appliquée par pulvérisation gazeuse à froid ou par pulvérisation gazeuse à chaud, une couche (11, 111) à proportion élevée de chrome est appliquée par chromage et/ou par une couche de base riche en chrome et ensuite une couche multiple (3, 13, 103) est déposée par dépôt physique en phase vapeur (PVD).
  14. Procédé selon la revendication 13,
    caractérisé en ce que
    la couche poreuse (101) est appliquée par pulvérisation gazeuse à froid.
  15. Procédé selon l'une des revendications 13. à 14,
    caractérisé en ce que
    la couche (2, 12, 102) de dureté supérieure est lissée après application et avant le revêtement suivait.
EP20110170936 2011-06-22 2011-06-22 Revêtement multicouches anti-usure et procédé de fabrication Not-in-force EP2537959B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20110170936 EP2537959B1 (fr) 2011-06-22 2011-06-22 Revêtement multicouches anti-usure et procédé de fabrication

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Application Number Priority Date Filing Date Title
EP20110170936 EP2537959B1 (fr) 2011-06-22 2011-06-22 Revêtement multicouches anti-usure et procédé de fabrication

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EP2537959A1 EP2537959A1 (fr) 2012-12-26
EP2537959B1 true EP2537959B1 (fr) 2013-12-25

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Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9909428B2 (en) * 2013-11-26 2018-03-06 General Electric Company Turbine buckets with high hot hardness shroud-cutting deposits
JP7398198B2 (ja) * 2019-03-12 2023-12-14 三菱重工業株式会社 タービン動翼及びコンタクト面製造方法
GB202000103D0 (en) * 2020-01-06 2020-02-19 Rolls Royce Plc Cold spraying
CN118127507B (zh) * 2024-05-06 2024-07-30 宁波爱柯迪科技产业发展有限公司 一种NiCr-Cr2C3-Cr2O3复合多层涂层及其制备方法

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9218858D0 (en) 1992-09-05 1992-10-21 Rolls Royce Plc High temperature corrosion resistant composite coatings
US6503340B1 (en) * 2000-08-02 2003-01-07 The Babcock & Wilcox Company Method for producing chromium carbide coatings
US20070099027A1 (en) * 2005-10-28 2007-05-03 Anand Krishnamurthy Wear resistant coatings
DE102005060243A1 (de) 2005-12-14 2007-06-21 Man Turbo Ag Verfahren zum Beschichten einer Schaufel und Schaufel einer Gasturbine
DE102006001864A1 (de) 2006-01-13 2007-07-19 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung
US8021742B2 (en) * 2006-12-15 2011-09-20 Siemens Energy, Inc. Impact resistant thermal barrier coating system
DE102008019891A1 (de) 2008-04-21 2009-10-22 Mtu Aero Engines Gmbh Erosionsschutzbeschichtung
DE102008023590A1 (de) 2008-05-14 2009-11-19 Mtu Aero Engines Gmbh Schutzschicht und Verfahren zum Herstellen einer Schutzschicht
RU2542870C2 (ru) 2009-05-26 2015-02-27 Сименс Акциенгезелльшафт Слоистая система покрытия со слоем mcralx и слоем, богатым по хрому, и способ ее получения
US20100304084A1 (en) 2009-05-29 2010-12-02 General Electric Company Protective coatings which provide erosion resistance, and related articles and methods
US20100304181A1 (en) 2009-05-29 2010-12-02 General Electric Company Protective coatings which provide erosion resistance, and related articles and methods

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