EP1754801B1 - Composant revetu - Google Patents

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Publication number
EP1754801B1
EP1754801B1 EP06015645.2A EP06015645A EP1754801B1 EP 1754801 B1 EP1754801 B1 EP 1754801B1 EP 06015645 A EP06015645 A EP 06015645A EP 1754801 B1 EP1754801 B1 EP 1754801B1
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EP
European Patent Office
Prior art keywords
platinum
proportion
component
weight
aluminium
Prior art date
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Expired - Fee Related
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EP06015645.2A
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German (de)
English (en)
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EP1754801A3 (fr
EP1754801A2 (fr
Inventor
Horst Pillhöfer
Thomas Dautl
Anton Albrecht
Thomas Cosack
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP1754801A2 publication Critical patent/EP1754801A2/fr
Publication of EP1754801A3 publication Critical patent/EP1754801A3/fr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • C23C10/06—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases
    • C23C10/16—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases more than one element being diffused in more than 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
    • C23C10/58—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in more than 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
    • 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
    • C23C28/04—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 only coatings of inorganic non-metallic material
    • C23C28/042—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 only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
    • 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
    • C23C28/04—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 only coatings of inorganic non-metallic material
    • C23C28/048—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 only coatings of inorganic non-metallic material with layers graded in composition or physical properties
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
    • F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y10T428/12618—Plural oxides
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • Y10T428/1275—Next to Group VIII or IB metal-base component
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12875—Platinum group metal-base component

Definitions

  • the invention relates to a component having a corrosion-resistant and / or oxidation-resistant coating comprising at least one platinum-aluminum substrate region.
  • the invention further relates to a corrosion-resistant and / or oxidation-resistant coating according to the preamble of claim 11.
  • Such components When operating components, in particular gas turbine components, at high temperatures, their free surfaces are exposed to highly corrosive and / or oxidizing conditions.
  • such components may consist of a nickel base superalloy.
  • coatings To protect against corrosion and / or oxidation such components are provided with coatings.
  • To provide a corrosion-resistant and / or oxidation-resistant coating on a component it is already state of the art to cut aluminum and optionally platinum onto a substrate surface of the component so as to provide a coating in the form of an aluminum substrate region or a platinum aluminum substrate region.
  • Platinum-aluminum coatings have the advantage over pure aluminum coatings of increased oxidation resistance and hot gas corrosion resistance, however, such platinum-aluminum coatings are brittle and therefore have a limited thermal-mechanical strength.
  • the EP 0 784 104 81 discloses a nickel-based alloy device having a platinum-aluminum substrate region, wherein to provide the platinum-aluminum substrate region, platinum is first deposited on a substrate surface of the device and then diffused into the substrate surface. Subsequently, the platinum coated member is aliquized to provide a platinum-aluminum substrate region having an integrated aluminum content of 18% to 24% by weight, an integrated content of 18% to 45% by weight. % and in the rest components of the substrate composition.
  • the Indian EP 0 784 104 B1 The disclosed platinum-aluminum substrate region or the device disclosed therein with such a coating has a relatively low ductility, resulting in a limited thermal mechanical strength (TMF), in particular a limited HCF strength and LCF Festigkelt. Due to the limited thermal-mechanical strength of the platinum-aluminum substrate region disclosed therein can form in the same cracks, which limit the durability of the coating.
  • TMF thermal mechanical strength
  • platinum-aluminum substrate region Another component with a platinum-aluminum substrate region is from the US 6,589,668 31 in which the platinum-aluminum substrate region disclosed therein comprises an inner aluminum diffusion zone and an outer platinum-aluminum zone having a single-phase structure. Also known from this prior art coating has a limited thermal-mechanical strength and thus durability.
  • the object of the present invention is to provide a novel component with a corrosion-resistant and / or oxidation-resistant coating and a novel corrosion-resistant and / or oxidation-resistant coating in the sense of better durability of the coating and thus of the component.
  • the platinum-aluminum substrate region in a peripheral zone has a diphasic structure with finely dispersed platinum-aluminum separations in a nickel-base mixed crystal and a single-phase structure in an inner zone disposed between the substrate surface of the device and the outer zone from a nickel-based mixed crystal.
  • the platinum-aluminum substrate region of the corrosion-resistant and / or oxidation-resistant coating of the component comprises at least two zones, namely an outer zone having a two-phase structure or duplex structure with finely dispersed pla tin-aluminum precipitates into a nickel base mixed crystal and an inner zone facing the substrate surface having a single phase structure of a nickel base mixed crystal.
  • the platinum aluminum substrate region according to the invention has good thermal-mechanical strength and thus provides effective and durable oxidation protection and corrosion protection even at high temperatures and mechanical stresses.
  • the platinum-aluminum substrate region of the corrosion-resistant and / or oxidation-resistant coating is suitable for the effective bonding of a ceramic heat protection layer on the platinum-aluminum substrate region.
  • the outer zone of the platinum-aluminum substrate region having the two-phase structure or duplex structure has finely dispersed, globulitic PtAl 2 precipitates sized between 0.1 ⁇ m and 3 ⁇ m in a mixed crystal of ⁇ -NiAl, the proportion of the two-phase structure or duplex structure is between 2.0 vol .-% and 40.0 vol .-% amounts, and wherein the A1 proportion in the mixed crystal is greater than 20.0 wt .-%.
  • the Al content in the nickel-base mixed crystal is at most 15.0 wt% and the Pt content in the nickel-base mixed crystal is at most 8.0 wt%.
  • a ceramic layer is applied to the platinum-aluminum substrate region, wherein an aluminum oxide intermediate layer is formed between the platinum-aluminum substrate region and the ceramic layer.
  • the ceramic layer is preferably in the form of a zirconium oxide layer the Al 2 O 3 intermediate layer has a proportion of at least 90.0% by volume of alpha-Al 2 O 3 having a rhombohedral crystal lattice structure and a maximum proportion of 10.0% by volume of gamma-Al 2 O 3 with a has cubic crystal lattice structure, and wherein the zirconium oxide layer comprises a proportion of not more than 8.0 wt .-% yttria.
  • the corrosion-resistant and / or oxidation-resistant coating according to the invention is defined in claim 11.
  • Fig. 1 shows a schematic cross section through an inventive component 10, on the substrate surface 11, a corrosion-resistant and oxidation-resistant coating in the form of a platinum-aluminum substrate portion 12 is applied.
  • the component 10 has a substrate composition based on nickel, preferably a directionally solidified or monocrystalline substrate composition having a nickel content between 18.0 wt .-% and 48.0 wt .-% with an aluminum content between 1.0 wt. -% and 8.0 wt .-%.
  • the platinum-aluminum substrate region 12 is applied to the substrate surface 11 of the component 10 in such a way that it forms two zones, namely an outer zone 13 and an inner zone 14 arranged between the outer zone 13 and the substrate surface 11 of the component 10
  • the outer zone 13 has a two-phase structure or duplex structure with finely dispersed platinum-aluminum precipitates in a nickel-based mixed crystal.
  • the inner zone 14, on the other hand, is a diffusion zone and has a single-phase structure of a nickel-based mixed crystal.
  • the outer zone 13 with the two-phase structure or duplex structure has feindispere, globulitic PtAl 2 precipitates having a size between 0.1 .mu.m and 3.0 .mu.m in a mixed crystal of ⁇ -NiAl, wherein the proportion of the two-phase structure or duplex structure is between 2.0% by volume and 40.0% by volume, and wherein the aluminum content in the mixed crystal is greater than 20.0% by weight.
  • the aluminum content in the nickel-based mixed crystal is max. 15.0 wt .-% and the platinum content in the nickel-based mixed crystal max. 8.0% by weight.
  • both in the outer zone 13 and in the inner diffusion zone 14 of the platinum-aluminum substrate region yttrium and / or hafnium may be present, wherein in both zones 13 and 14, the yttrium content max. 1.5 wt .-% and / or the hafnium content also max. 1.5 wt .-% is.
  • the size of the PtAl 2 precipitates is between 0.1 ⁇ m and 1.0 ⁇ m
  • the proportion of the two-phase structure or duplex structure is between 2.0% by volume and 20 , 0 vol .-%
  • the proportion of aluminum in the solid solution is greater than 25 wt .-%.
  • the aluminum content is preferably max. 10.0 wt .-% and the platinum content max. 1.0 wt .-%, wherein in a particularly preferred embodiment, the platinum content in the inner diffusion zone 14 of the platinum-aluminum substrate region 12 max. 0.1 wt .-% is.
  • a component 10 is provided with a substrate composition, which is formed as a nickel-based alloy.
  • the component 10 may be, for. Example, to a blade of a gas turbine made of a single crystal nickel-based alloy of the type SC 2000, the over 5.0 wt .-% cobalt, 10.0 wt .-% chromium, 5.0 wt .-% aluminum, 1.5 wt % Titanium, 12.0 wt% tantalum, 4.0 wt% tungsten and the balance nickel.
  • the prepared component 10 is cleaned in the region of the subastrate surface 11, preferably by abrasive blasting with an aluminum oxide blasting agent having a particle size between 5 .mu.m and 150 .mu.m, preferably between 45 .mu.m and 75 .mu.m.
  • the abrasive blasting is preferably carried out in a multi-jet blasting machine at a pressure between 2 bar and 5 bar, preferably at a pressure of 3 bar, wherein a so-called degree of coverage during abrasive blasting is between 400% and 1000%, preferably 800%.
  • a layer thickness of between 5 ⁇ m and 10 ⁇ m is abraded off abradingly on the substrate surface 11.
  • a deposition of platinum on the cleaned substrate surface 11 of the component 10 in which case a platinum layer thickness between 1 .mu.m and 10 .mu.m, preferably between 2 .mu.m and 4 ⁇ m, forms.
  • the platinum then diffuses into the substrate surface, the diffusion preferably being in the form of diffusion annealing at a temperature between 960 ° C. and 1160 ° C., preferably at a temperature between 1000 ° C. and 1,100 ° C, is performed.
  • the holding period of the diffusion annealing for the diffusion of the platinum into the substrate surface 11 is relatively short and is between 5 minutes and 60 minutes, preferably between 5 minutes and 15 minutes.
  • Aluminum is subsequently deposited on the substrate surface 11 coated with platinum in a further step of the method according to the invention.
  • the deposition of the aluminum takes place thermochemically in a high activity gas phase process in an atmosphere of aluminum monohalides, wherein the proportion of aluminum monohalides in the atmosphere is at least 15 vol .-%, wherein the pressure during deposition 10 mbar to 800 mbar Normal pressure or ambient pressure is, and wherein the temperature between 950 ° C and 1140 ° C is.
  • the aluminum is diffused at an activity thereof of at least 50 atomic% with respect to pure nickel, the diffusion being at a temperature at least 10 ° C. below the annealing temperature of the platinum, and the Holding period for the in-diffusion of aluminum between 180 min and 360 min, preferably between 210 min and 330 min, is.
  • the platinum-aluminum substrate region 12 forms with a thickness of approximately 60 ⁇ m.
  • the coating produced according to the invention from the in Fig. 1 illustrated platinum-aluminum substrate area 12 therefore has a good durability on the component 10.
  • Fig. 2 shows a second embodiment of a component according to the invention with a corrosion-resistant and / or oxidation-resistant coating, wherein in the embodiment of the Fig. 2 the component 10 next to the platinum-aluminum substrate region 12, which in turn is applied to the substrate surface 11 of the component 10 and has the two zones 13 and 14, comprises a ceramic layer 15, wherein between the ceramic layer 15 and the outer layer 13th of the platinum-aluminum substrate region 12, an aluminum oxide intermediate layer 16 is formed.
  • the component 10 next to the platinum-aluminum substrate region 12 which in turn is applied to the substrate surface 11 of the component 10 and has the two zones 13 and 14, comprises a ceramic layer 15, wherein between the ceramic layer 15 and the outer layer 13th of the platinum-aluminum substrate region 12, an aluminum oxide intermediate layer 16 is formed.
  • the alumina interlayer 16 which adjoins the outer zone 13 of the platinum-aluminum substrate region 12, is implemented as an Al 2 O 3 interlayer and has a minimum of 90.0% by volume alpha-Al content 2 O 3 with a rhombohedral crystal lattice structure and a proportion of max. 10.0% by volume of gamma-Al 2 O 3 having a cubic crystal lattice structure, the lattice structures having similar lattice sizes. The deviation of the lattice sizes of the crystal lattice structures is at most about 2%.
  • the ceramic layer 15 is applied, which is used as a zirconium oxide layer with a proportion of max. 8.0 wt .-% yttrium oxide is formed.
  • the ceramic layer 15 has a columnar structure and has a cubic-tetragonal crystal lattice, the ceramic layer 15 adhering very well to the aluminum oxide interlayer 16.
  • the aluminum oxide intermediate layer 16 has a thickness of between 0.02 ⁇ m and 0.8 ⁇ m, the ceramic layer 15 has a thickness of between 100 ⁇ m and 200 ⁇ m.
  • the height-to-width ratio of the stems is a minimum of 10, with the length of the stems being between 0.05 ⁇ m and 0.5 ⁇ m.
  • inventive component with the inventive, corrosion-resistant and oxidation-resistant coating is prepared according to a concrete embodiment in that in a first step as a component z. B. a blade of a gas turbine is provided from a directionally solidified nickel-based alloy material, for. B. from the nickel-based alloy Rene 142 with 12.0 wt .-% cobalt, 6.8 wt .-% chromium, 6.1 wt .-% aluminum, 6.3 wt .-% tantalum, 1.5 wt. % Molybdenum, 5.0% by weight tungsten, 1.5% by weight hafnium, 2.8% by weight rhenium and the remainder nickel.
  • the substrate surface 11 thereof is cleaned, preferably by abrasive blasting with corundum in a particle size between 20 microns and 100 microns at a pressure of 2.5 bar and a degree of coverage in a multi-jet blasting plant of preferably 800% ⁇ 200th %.
  • a layer thickness between 3 .mu.m and 10 .mu.m is abraded abradingly on the substrate surface 11.
  • platinum is then deposited with a layer thickness of preferably 2 .mu.m to 4 .mu.m on the substrate surface 11, wherein subsequent to the deposition of platinum, an indiffusing platinum at a temperature of about 1080.degree. C. and a Holding time of about 15 minutes. he follows.
  • a platinum-aluminum substrate region 12 is then formed with a thickness of about 60 .mu.m, wherein in the outer zone 13 of the platinum-aluminum substrate region 12, the proportion of the two-phase structure or duplex structure in about 15 vol .-% and the finely dispersed, globulitic PtAl 2 precipitates have a size of about 0.3 ⁇ m.
  • the platinum-aluminum substrate portion 12 is cleaned by abrasive blasting, whereby the mechanical abrasion blasting from the outer zone 13 of the platinum-aluminum substrate portion 12 has a film thickness of is removed in about 2 microns.
  • the ablated layer thickness can be between 0.5 ⁇ m and 8 ⁇ m, preferably between 1 ⁇ m and 3 ⁇ m.
  • the mechanical abrasive blasting is done preferably with aluminum oxide particles having a particle size between 10 .mu.m and 150 .mu.m, preferably between 10 .mu.m and 50 .mu.m.
  • the jet pressure is less than 3 bar, preferably 2.5 bar, with the abrasive blasting with a coverage between 300% and 1,500%, preferably with a coverage between 300% and 500%, worked.
  • thermo-oxidative treatment of the coated with the platinum-aluminum substrate region 12 and cleaned component then takes place to form the aluminum oxide intermediate layer 16, namely, that under high vacuum at a pressure of about 10 -4 mbar heating up a temperature of about 900 ° C, wherein then under low vacuum or partial vacuum at a pressure of max. 5 x 10 -2 mbar a temperature between 900 ° C and 1100 ° C for a time of about 10 minutes is maintained.
  • low vacuum or partial vacuum of preferably 10 -3 mbar there is an atmosphere of oxygen and argon or helium, wherein the oxygen content between 25 vol .-% and 60 vol .-% and therefore the argon content or helium content between 75 vol. % and 40 vol.%.
  • the alumina intermediate layer 16 can be provided, which is preferably made of pure alpha-Al 2 O 3 .
  • the ceramic layer 15 is applied to the aluminum oxide interlayer 16, namely by zirconium oxide Zr 2 O 3 having a proportion of max. 8.0 wt .-% yttria (Y 2 O 3 ) is deposited.
  • the deposition of the ceramic layer 15 is carried out under thermally oxidizing conditions, wherein a temperature between 900 ° C and 1100 ° C for a predetermined period of about 15 minutes at a low vacuum or partial vacuum is maintained. Again, there is an atmosphere of oxygen and argon and helium, with the oxygen content between 25 vol .-% and 60 vol .-%.
  • the vapor deposition of the ceramic layer takes place during oscillating and / or tumbling movement of the component 11 in a vapor cone of the ceramic material.
  • the deposition of the ceramic layer 15 can also be carried out as a sol-gel process or CVD process or PVD process.
  • FIG. 2 shows the good durability of the platinum-aluminum substrate region 12 and thus of the entire corrosion-resistant and / or oxidation-resistant coating on the component 10 using the example of a diagram, FIG. wherein on the horizontal axis 17, the trial time or process time and on the vertical axis 18, a weight change of a coated component according to the invention is applied.
  • Curve 19 represented by a solid line corresponds to a component coated in accordance with the invention
  • the curve 20 shown by dashed lines corresponds to a component coated according to the prior art. So can Fig.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Physical Vapour Deposition (AREA)

Claims (11)

  1. Composant avec un revêtement comprenant au moins une région de substrat en platine-aluminium, résistant à la corrosion et/ou résistant à l'oxydation, dans lequel le composant présente une surface de substrat et une composition de substrat à base de nickel avec, dans la région de la surface de substrat du composant, une région de substrat en platine-aluminium réalisée par dépôt de platine (Pt) et d'aluminium (Al) sur la surface de substrat, caractérisé en ce que la région de substrat en platine-aluminium (12) présente, dans une zone extérieure (13), une structure à deux phases ou une structure duplex avec des précipités finement dispersés de platine-aluminium dans un cristal mixte à base de nickel, et en ce que la région de substrat en platine-aluminium (12) présente dans une zone intérieure (14), qui est disposée entre la surface de substrat (11) du composant et la zone extérieure (13), une structure à une phase en un cristal mixte à base de nickel.
  2. Composant selon la revendication 1, caractérisé en ce que la zone extérieure (13) avec la structure à deux phases ou avec la structure duplex présente des précipités globulaires finement dispersés de PtAl2 présentant une taille comprise entre 0,1 µm et 3,0 µm dans un cristal mixte en β-NiAl, dans lequel la part de la structure à deux phases ou de la structure duplex se situe entre 2,0 % en volume et 40,0 % en volume, et dans lequel la part de Al dans le cristal mixte est supérieure à 20,C % en poids.
  3. Composant selon la revendication 2, caractérisé en ce que la zone extérieure (13) avec la structure à deux phases ou avec la structure duplex présente des précipités globulaires finement dispersés de PtAl2 présentant une taille comprise entre 0,1 µm et 1,0 µm dans un cristal mixte à base de β-NiAl, dans lequel la part de la structure à deux phases ou de la structure duplex se situe entre 2,0 % en volume et 20,0 en volume, et dans lequel la part de Al dans le cristal mixte est supérieure à 25,0 % en poids.
  4. Composant selon la revendication 1 ou 2, caractérisé en ce que dans la zone intérieure (14), qui est une zone de diffusion, la part de Al dans le crystal mixte à base de nickel vaut au maximum 15,0 % en poids et la part de Pt dans le cristal mixte à base de nickel vaut au maximum 8 % en poids.
  5. Composant selon la revendication 4, caractérisé en ce que dans la zone intérieure (14), qui est une zone de diffusion, la part de Al dans le cristal mixte à base de nickel vaut au maximum 10, % en poids.
  6. Composant selon une ou plusieurs des revendications 1 à 5, caractérisé en ce que la région de substrat en platine-aluminium présente, dans la zone extérieure (13) et/ou dans la zone intérieure (14), une part d'yttrium de 1,5 % en poids au maximum et/ou une part de hafnium de 1,5 en poids au maximum.
  7. Composant selon une ou plusieurs des revendications 1 à 6, caractérisé en ce qu'une couche céramique (15) est déposée sur la région de substrat en platine-aluminium (12), dans lequel une mince couche intermédiaire d'oxyde d'aluminium (16) est formée entre la région de substrat en platine-aluminium (12) et la couche céramique (15).
  8. Composant selon la revendication 7, caractérisé en ce que la couche intermédiaire d'oxyde d'aluminium (16) est formée par une couche intermédiaire de Al2O3 avec une part d'au moins 90,0 % en volume de a-Al2O3 avec une structure de réseau cristallin rhomboédrique et une part de 10,0 % en volume au maximum de γ-Al2O3 avec une structure de réseau cristallin cubique.
  9. Composant selon la revendication 7 ou 8, caractérisé en ce que la couche céramique (15) est formée par une couche d'oxyde de zirconium avec une part de 8,0 % en poids au maximum d'oxyde d'yttrium.
  10. Composant selon une ou plusieurs des revendications 1 à 9, caractérisé en ce que le composant présente une composition de substrat à solidification dirigée ou monocristalline à base de nickel avec une part de nickel comprise entre 18,0 % % en poids et 48,0 % en poids et une part d'aluminium comprise entre 1,0 % en poids et 8,0 %en poids.
  11. Revêtement résistant à la corrosion et/ou résistant à l'oxydation pour un composant, en particulier un composant de turbine à gaz, dans lequel le revêtement comprend au moins une région de substrat en platine-aluminium, caractérisé par des caractéristiques selon une ou plusieurs des revendications 1 à 9.
EP06015645.2A 2005-08-02 2006-07-27 Composant revetu Expired - Fee Related EP1754801B1 (fr)

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Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2604570A1 (fr) * 2006-10-05 2008-04-05 General Electric Company Methode pour former un revetement isolant
DE102007008278A1 (de) * 2007-02-20 2008-08-21 Mtu Aero Engines Gmbh Beschichtung für Gasturbinenbauteile sowie Verfahren und Vorrichtung zur Bereitstellung einer Beschichtung
DE102007025697A1 (de) * 2007-06-01 2008-12-04 Mtu Aero Engines Gmbh Verfahren zum Einstellen der Anzahl der Phasen einer PtAI-Schicht eines Gasturbinenbauteils sowie Verfahren zum Erzeugen einer einphasigen PtAI-Schicht an einem Gasturbinenbauteil
DE102009010109A1 (de) 2009-02-21 2010-09-23 Mtu Aero Engines Gmbh Herstellung einer Turbinenblisk mit einer Oxikations- bzw. Korrosionsschutzschicht
DE102009010110B4 (de) * 2009-02-21 2014-08-28 MTU Aero Engines AG Erosionsschutz-Beschichtungssystem für Gasturbinenbauteile
KR101598676B1 (ko) * 2010-12-03 2016-02-29 일렉트롤리틱 오존 인코퍼레이티드 오존 생성을 위한 전해질 전지
US8807955B2 (en) * 2011-06-30 2014-08-19 United Technologies Corporation Abrasive airfoil tip
GB2519047B (en) * 2012-08-14 2018-08-22 Snecma A method of measuring the temperature reached by a part, in particular a turbine engine part
MX2023002015A (es) 2020-08-18 2023-04-11 Enviro Metals Llc Refinamiento metálico.
US20220081763A1 (en) * 2020-09-17 2022-03-17 Applied Materials, Inc. Aluminum oxide protective coatings on turbocharger components and other rotary equipment components

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5514482A (en) 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
US5500252A (en) * 1992-09-05 1996-03-19 Rolls-Royce Plc High temperature corrosion resistant composite coatings
US5658614A (en) 1994-10-28 1997-08-19 Howmet Research Corporation Platinum aluminide CVD coating method
US6066405A (en) 1995-12-22 2000-05-23 General Electric Company Nickel-base superalloy having an optimized platinum-aluminide coating
US5897966A (en) * 1996-02-26 1999-04-27 General Electric Company High temperature alloy article with a discrete protective coating and method for making
EP1123987A1 (fr) 2000-02-11 2001-08-16 General Electric Company Revêtements réparables d'aluminures à diffusion
US6340500B1 (en) * 2000-05-11 2002-01-22 General Electric Company Thermal barrier coating system with improved aluminide bond coat and method therefor
US6589668B1 (en) * 2000-06-21 2003-07-08 Howmet Research Corporation Graded platinum diffusion aluminide coating
US6881452B2 (en) 2001-07-06 2005-04-19 General Electric Company Method for improving the TBC life of a single phase platinum aluminide bond coat by preoxidation heat treatment
DE10336989B4 (de) 2003-08-12 2006-11-09 Mtu Aero Engines Gmbh Verfahren zur Herstellung von Heissgas-Korrosionsschutzschichten
DE10350727A1 (de) 2003-10-30 2005-06-02 Mtu Aero Engines Gmbh Bauteil mit einem Platin-Aluminium-Substratbereich, Platin-Aluminium-Beschichtung und Herstellverfahren
DE10355234A1 (de) 2003-11-26 2005-06-30 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer korrosionsbeständigen und oxidationsbeständigen Beschichtung sowie Bauteil mit einer solchen Beschichtung
US7229701B2 (en) * 2004-08-26 2007-06-12 Honeywell International, Inc. Chromium and active elements modified platinum aluminide coatings

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US7655321B2 (en) 2010-02-02
EP1754801A3 (fr) 2008-04-02
US20080166589A1 (en) 2008-07-10
EP1754801A2 (fr) 2007-02-21
DE102005036162A1 (de) 2007-02-08

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