EP2695964A1 - Couche de protection adaptée au composant - Google Patents

Couche de protection adaptée au composant Download PDF

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Publication number
EP2695964A1
EP2695964A1 EP12179980.3A EP12179980A EP2695964A1 EP 2695964 A1 EP2695964 A1 EP 2695964A1 EP 12179980 A EP12179980 A EP 12179980A EP 2695964 A1 EP2695964 A1 EP 2695964A1
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EP
European Patent Office
Prior art keywords
chromium
component
layer
different
carried out
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.)
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EP12179980.3A
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German (de)
English (en)
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EP2695964B1 (fr
Inventor
Horst Pillhöfer
Erwin Bayer
Thomas Dautl
Stefan Müller
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MTU Aero Engines AG
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MTU Aero Engines AG
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Priority to EP12179980.3A priority Critical patent/EP2695964B1/fr
Priority to US13/962,360 priority patent/US20140044938A1/en
Publication of EP2695964A1 publication Critical patent/EP2695964A1/fr
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
    • 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
    • C23C10/02—Pretreatment of the material to be coated
    • 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
    • C23C10/32—Chromising
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/38—Chromising
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/38—Chromising
    • C23C10/40—Chromising of ferrous surfaces
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/48—Aluminising
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/48—Aluminising
    • C23C10/50—Aluminising of ferrous surfaces
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • C23C10/54—Diffusion of at least chromium
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • C23C10/54—Diffusion of at least chromium
    • C23C10/56—Diffusion of at least chromium and at least aluminium
    • 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
    • C23C10/60—After-treatment
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24802—Discontinuous or differential coating, impregnation or bond [e.g., artwork, printing, retouched photograph, etc.]
    • Y10T428/24917—Discontinuous or differential coating, impregnation or bond [e.g., artwork, printing, retouched photograph, etc.] including metal layer

Definitions

  • the present invention relates to a method for producing a protective layer for protecting a component against high temperatures and aggressive media and to a component having such a protective layer, wherein the protective layer comprises aluminum and chromium. Moreover, the invention relates to a component with a corresponding protective layer, in particular a component for a gas turbine or an aircraft engine.
  • turbomachines such as stationary gas turbines or aircraft engines
  • components such as vanes or blades are exposed to both high temperatures and aggressive media or atmospheres that cause differential damage such as particulate erosion, corrosion and high temperature oxidation. Accordingly, it is necessary to protect the components as possible against all these damages, which may have to compromise compromised, since protective measures that are promising for one type of injury, even a strong damage may be exposed by other damage mechanisms.
  • the process should be easy to carry out and provide the protective layer effective protection against corrosion and oxidation.
  • the invention takes up the idea that different protective layers must be provided on a component which is subjected to different damage mechanisms. Contrary to the state of the art, separated in the elaborate process different However, layers are produced, the present invention proposes to form an aluminum and chromium-containing layer, which may be formed differently in different areas of the protective layer, but whose different areas can be prepared in common manufacturing steps. Corresponding aluminum-chromium layers can namely be adjusted by varying the chromium content to different oxidation and corrosion attacks, so that by aluminum-chromium layers, which in particular have different chrome components, a component effective protection against different damage mechanisms can be imparted. At the same time, the aluminum-chromium layers offer the advantage that they can be produced with different amounts of chromium in locally different areas in a single step.
  • aluminum-chromium layers according to the invention are produced by carrying out inchromatization of the component surface to be protected in a first partial step and alitating in a second partial step.
  • the inchromization and / or alitination can be carried out simultaneously in different local areas of the component surface to be protected, but in such a way that different areas arise in the protective layer in accordance with the different protection requirements.
  • the deposition of the chromium in the first substep of the inchromatization can be carried out by means of thermochemical methods, thermophysical methods, physical methods or electrochemical methods.
  • Thermochemical processes are gas diffusion deposits in which chromium is provided using temperature and chemical reactions on the component surface, so that the chromium can diffuse into the component and / or deposit on it.
  • the use of temperature causes evaporation with corresponding deposition of chromium.
  • deposition of chromium from an electrolyte is effected while providing an electrical potential.
  • the deposition of chromium can also be done by means of dispersion coating. A combination of the latter two methods is also conceivable.
  • a support layer by means of chemical and / or electrochemical deposition of chromium and other constituents, such as nickel, and additionally incorporated particles.
  • the diffusion of chromium into the component surface to form a chromium-rich layer after application to the component surface to be protected can be carried out by a corresponding heat treatment, which also in thermochemical and thermophysical processes, in which the application is already carried out at correspondingly high temperatures and therefore already permitting diffusion of the chromium in the component surface, in addition a more extensive heat treatment for further diffusion of the chromium into deeper component regions can be carried out.
  • different chromium contents can be deposited to form the different protective layer regions in the different regions, for example by applying chromium-containing materials in different amounts or with different concentrations of chromium.
  • the deposition of different chromium contents can be carried out in such a way that a chromium content of 15% by weight to 100% by weight can be present in the chromium enriched layer formed.
  • chromium-enriched layers can also be produced at different thicknesses, and in particular the layer thicknesses can vary in the range from 5 ⁇ m to 150 ⁇ m.
  • chromanization can be carried out with high chromium activity, wherein the chemical activity can be ⁇ 0.4 and 40 percent, respectively. This can be realized, for example, by powder packing or gas phase inchromating.
  • the chromation can be carried out in particular by a temperature treatment in the presence of liquid, chromium-rich slip layers, wherein the slip can comprise chromium-containing powders with activators and binders.
  • Suitable binders are alcohols or other solvents, while halides can be used as the activator.
  • the slip can be applied by physical means such as brushing or spraying.
  • thermal and / or thermochemical treatment can be carried out in a temperature range of 1000 ° C to 1180 ° C , in particular 1050 ° C to 1100 ° C for times of 2 to 20 hours, in particular 10 to 15 hours, a chromium-rich layer with a layer thickness of 10 .mu.m to 150 .mu.m and a chromium content of greater than or equal to 40 wt .-%, in particular 50 Wt .-% to 95 wt .-% are formed.
  • the chromium-rich layer in this case has an outer ⁇ -chromium partial layer and an inner mixed crystal layer with essentially chromium and the main component of the alloy of the coated component, e.g. Nickel on.
  • the chromation in the first sub-step at a temperature of 1000 ° C to 1180 ° C, in particular 1050 ° C to 1130 ° C at a period of 1 to 20 hours, in particular 10 to 15 hours perform.
  • the base material thus treated for example a component of a gas turbine or an aircraft engine
  • the component is packed, for example, in a powder package with high aluminum activity (chemical activity) in the range greater than or equal to 0.15 or 15% and thermally or thermochemically treated at temperatures greater than 1050 ° C for a period of 2 to 14 hours.
  • gas phase alitization can also be used. In particular, areas without Alitieren remain if these areas are covered accordingly.
  • the aluminum activity can range from 0.15 to 0.35.
  • Suitable powder packings are mixtures of aluminum oxide powder, aluminum powder and a halide activator, so that aluminum in the order of 10% by weight to 30% by weight can diffuse into the layer. Alitating can also produce locally different protective layers by locally differently used aluminum activities. Here, either only the Alit réelle evenly generated Cr - rich Layers are made locally different or combined with the above-described locally different chromating.
  • a second alitization may be carried out with a lower chemical aluminum activity, the aluminum activity being selectable in the range of 0.05 to 0.3.
  • the aging temperature in this second Alitier Marin may be greater than or equal to 1050 ° C and the aging time 3 to 20 hours.
  • a diffusion annealing may be performed at a temperature greater than or equal to 1050 ° C. for a period of 2 to 8 hours.
  • PVD physical vapor deposition
  • CVD chemical vapor deposition
  • electrodeposition electrodeposition and / or direct application of a substance before, during or after chromating and / or alitizing.
  • one or more elements of the group comprising platinum, palladium, hafnium, zirconium, yttrium and silicon are applied.
  • one or more of these elements can be introduced into the layer so as to additionally influence the layer properties positively.
  • components such as stationary gas turbine or aeroengine turbine blades may be manufactured according to the above method having a protective layer with large amounts of chromium and aluminum, the protective layer having different areas characterized by their composition in terms of chromium and / or or aluminum content.
  • the protective layer has at least two distinct regions each comprising different surface layers.
  • the surface layer that is the outer layer of the component that comes into contact with the surrounding atmosphere, may be either a high chromium AlCr layer, an AlCr layer with medium aluminum contents and low chromium contents or a layer with average chromium and aluminum contents.
  • the FIG. 1 shows a turbine blade, as it can be used for example in a stationary gas turbine or in an aircraft engine use.
  • the turbine blade 1 has an airfoil 2, an inner shroud 3 and an outer shroud 4.
  • a temperature-location diagram is shown above the turbine blade 1, which shows the temperature profile over the blade during use. As can be seen from the graph, lower temperatures are to be expected outside the gas flow area at the inner shroud 3 and at the outer shroud 4 than at the airfoil area 2.
  • At the transition points 5.6 from the airfoil 2 to the inner shroud 3 and from the airfoil 2 to the outer shroud 4 respectively mean temperatures up.
  • the turbine blade 1 is provided with different protective layers, wherein protective coatings based on chromium and in particular high-chromium AlCr layers are formed in the inner cover tape area or outer cover tape area, while in the airfoil area 2 protective layers based on aluminum or platinum - aluminum, and in particular AlCr layers with a low chromium content, while in the transitional areas 5, 6 aluminum - chromium layers with medium chromium content are applied.
  • the high chromium aluminum chromium layers form a first outer surface layer having chromium contents in the range of 40 to 90% by weight and aluminum contents in the range of 5 to 35% by weight.
  • chromium contents in the range of 40 to 90% by weight and aluminum contents in the range of 5 to 35% by weight.
  • main constituents of the base material in particular the main component, such as nickel, cobalt or iron depending on whether the base material of the component to be protected is a nickel-based alloy, cobalt-based alloy or iron-based alloy.
  • the low chromium AlCr layers form another, second outer surface layer having chromium contents in the range of 5% to 15% by weight and aluminum contents in the range of 5% to 35% by weight.
  • the proportion of components of the base alloy and in particular the main component of the base alloy is in the range of 50 wt .-% to 75 wt .-%.
  • the intermediate chromium-content aluminum-chromium layers form another, third outer surface layer, the chromium contents in the range of 15 wt .-% to 40 wt .-%, aluminum contents of 5 wt .-% to 35 wt .-%, preferably 15 wt .-% to 35 wt .-%, and proportions of the base alloy has up to 70 wt .-%.
  • first, second and third surface layers are illustrated by way of example of a nickel base alloy as the base material of the turbine blade.
  • first surface layers in the form of high chromium aluminum-chromium layers are provided, which are located in the region A near the chrome tip in the shown ternary state diagram.
  • second surface layers in the form of low chromium alloyed aluminum-chromium layers are provided, which are located in the region T near the nickel corner in the ternary state diagram.
  • AlCr layers having medium chromium composition used as third surface layers for the gas channel transition regions 5,6 which exhibit both high temperature oxidation and corrosion.
  • a coating of the entire component e.g. the turbine blade, with a layer of aluminum and chromium according to the invention has been described.
  • a protective layer according to the invention with aluminum-chromium layers is also possible in combination with other known protective layers.
  • the term coating does not only mean a deposit of the deposited aluminum and chromium on the original component surface, but the protective layer can also extend inwards from the original component surface into the material interior.
  • the above method may be applied to gas turbine or aircraft engine components.
  • the component may be formed of an alloy that is metallic Main component having the largest proportion of the alloy, with a protective layer for protection against high temperatures and aggressive media, the protective layer comprising chromium and aluminum and in particular has been prepared by a method according to any one of the preceding claims, and wherein the protective layer different Areas which differ in their composition in terms of chromium and / or aluminum content.
  • the protective layer may comprise at least two different regions each having a surface layer from the group comprising a first surface layer having a chromium content of greater than or equal to 40% by weight, an aluminum content of from 5% to 35% by weight and a proportion the main component of the component less than or equal to 55 wt .-%, a second surface layer having a chromium content of 5 wt .-% to 15 wt .-%, an aluminum content of 10 wt .-% to 35 wt .-% and a proportion of Main component of the component from 50% by weight to 75% by weight, and a third surface layer with a chromium content of 15% by weight to 40% by weight, an aluminum content of 15% by weight to 35% by weight. and a content of the main component of the component less than or equal to 70% by weight.
  • the chromium content may range from 40% to 90%, preferably greater than or equal to 50% and / or the aluminum content in the range from 5% to 25% by weight. -% and / or the proportion of the main component of the component be less than or equal to 30 wt .-%.
  • the Al content of the second surface layer is 20 wt% and 35 wt%.
  • the chromium content may be in the range of 20% by weight to 40% by weight and / or the aluminum content in the range of 20% by weight to 35% by weight.
  • the different regions of the protective layer are selected according to the temperature load and / or the acting atmosphere during operation of the component.
  • the component can be a running or guide blade of a turbomachine, in particular a gas turbine or an aircraft engine, which is at least partially coated with the protective layer, wherein in particular additional other layer systems can be provided.
  • the first surface layer may be disposed in areas of predominant sulfidation loading and / or operating temperature ranges in the range of 550 ° C to 900 ° C.
  • the second surface layer of the component may be placed in areas of predominant oxidation load and / or areas of operating temperatures greater than or equal to 900 ° C.
  • the third surface layer may be placed in areas of combined stress with oxidation and sulfidation.
  • the first surface layer in the foot and / or shroud region of the blade and / or the second surface layer in the blade region of the blade and / or the third surface layer in the transition region foot / blade and / or blade / shroud be arranged.
  • the layer thickness of the protective layer is 10 ⁇ m to 250 ⁇ m, in particular 40 ⁇ m to 150 ⁇ m.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Wood Science & Technology (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP12179980.3A 2012-08-10 2012-08-10 Couche de protection adaptée au composant Active EP2695964B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP12179980.3A EP2695964B1 (fr) 2012-08-10 2012-08-10 Couche de protection adaptée au composant
US13/962,360 US20140044938A1 (en) 2012-08-10 2013-08-08 Process for producing a COMPONENT-MATCHED PROTECTIVE LAYER and component having such a protective layer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12179980.3A EP2695964B1 (fr) 2012-08-10 2012-08-10 Couche de protection adaptée au composant

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EP2695964A1 true EP2695964A1 (fr) 2014-02-12
EP2695964B1 EP2695964B1 (fr) 2020-05-06

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Cited By (3)

* Cited by examiner, † Cited by third party
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EP3438414A1 (fr) * 2017-08-04 2019-02-06 MTU Aero Engines GmbH Aube pour turbomachine dotée des différentes couches de protection et procédé de fabrication
DE102018213395A1 (de) * 2018-08-09 2020-02-13 MTU Aero Engines AG Verfahren zum versehen einer metallischen oberfläche mit einer chrom-diffusionsschutzschicht

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US10053779B2 (en) 2016-06-22 2018-08-21 General Electric Company Coating process for applying a bifurcated coating
US10077494B2 (en) 2016-09-13 2018-09-18 General Electric Company Process for forming diffusion coating on substrate
FR3102775B1 (fr) * 2019-11-05 2022-04-22 Safran Piece d'aeronef en superalliage comprenant un canal de refroidissement

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EP3438414A1 (fr) * 2017-08-04 2019-02-06 MTU Aero Engines GmbH Aube pour turbomachine dotée des différentes couches de protection et procédé de fabrication
DE102017213553A1 (de) 2017-08-04 2019-02-07 MTU Aero Engines AG Schaufel für strömungsmaschine mit verschiedenen diffusionsschutzschichten und verfahren zur herstellung
US10914181B2 (en) 2017-08-04 2021-02-09 MTU Aero Engines AG Blade or vane for turbomachine with different diffusion protective coatings and method for manufacture thereof
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CN107607577B (zh) * 2017-09-28 2020-04-10 中国煤炭地质总局水文地质局 一种地层换热能力的热物性测试装置
DE102018213395A1 (de) * 2018-08-09 2020-02-13 MTU Aero Engines AG Verfahren zum versehen einer metallischen oberfläche mit einer chrom-diffusionsschutzschicht

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