EP1754801A2 - Composant revetu - Google Patents

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Publication number
EP1754801A2
EP1754801A2 EP06015645A EP06015645A EP1754801A2 EP 1754801 A2 EP1754801 A2 EP 1754801A2 EP 06015645 A EP06015645 A EP 06015645A EP 06015645 A EP06015645 A EP 06015645A EP 1754801 A2 EP1754801 A2 EP 1754801A2
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EP
European Patent Office
Prior art keywords
platinum
aluminum
component
nickel
substrate region
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06015645A
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German (de)
English (en)
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EP1754801A3 (fr
EP1754801B1 (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 GmbH
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Publication of EP1754801A2 publication Critical patent/EP1754801A2/fr
Publication of EP1754801A3 publication Critical patent/EP1754801A3/fr
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Publication of EP1754801B1 publication Critical patent/EP1754801B1/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 and to a method for producing such a corrosion-resistant and / or oxidation-resistant coating according to the preamble of claim 12.
  • 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 deposit on a substrate surface of the component aluminum and optionally platinum 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 limited thermal-mechanical strength.
  • the EP 0 784 104 B1 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 platinum 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 component disclosed there 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 strength. Due to the limited thermo-mechanical strength of the platinum-aluminum substrate region disclosed therein, cracks which limit the durability of the coating can form in the same.
  • TMF thermal mechanical strength
  • platinum-aluminum substrate region Another component with a platinum-aluminum substrate region is from the US 6,589,668 B1 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 present invention is based on the problem of creating a novel component with a corrosion-resistant and / or oxidation-resistant coating, a novel corrosion-resistant and / or oxidation-resistant coating and a novel method for producing a corrosion-resistant and / or oxidation-resistant coating.
  • the platinum-aluminum substrate region has a two-phase structure or duplex structure with finely dispersed platinum-aluminum precipitates in a nickel-based mixed crystal in an outer zone and a single-phase structure in an inner zone which is arranged between the substrate surface of the component 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 platinum-aluminum precipitates in a nickel-based mixed crystal and a inner, the substrate surface facing zone with a single-phase structure of a nickel-based 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 loads.
  • the platinum-aluminum substrate region of the corrosion-resistant and / or oxidation-resistant coating is suitable for effectively bonding a ceramic heat-insulating layer on the platinum-aluminum substrate region.
  • the outer zone of the platinum-aluminum substrate region having the two-phase structure or duplex structure finely dispersed, 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 Two-phase structure or duplex structure is between 2.0 vol .-% and 40.0 vol .-%, and wherein the Al content 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 having 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 vol gamma Al 2 O 3 having a cubic crystal lattice structure, and wherein the zirconia layer comprises a maximum of 8.0 wt% yttria.
  • the corrosion-resistant and / or oxidation-resistant coating according to the invention is in claim 11 and the method according to the invention for producing a corrosion-resistant and / or oxidation-resistant coating is defined in claim 12.
  • 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.
  • the procedure in a concrete exemplary embodiment is that in a first step, a component 10 having a substrate composition is provided 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 platinum-aluminum substrate region 12 shown in FIG. 1 may be provided with the zones 13 and 14, wherein the platinum-aluminum substrate region 12 has high oxidation resistance and corrosion resistance even at high temperatures as well as an excellent thermal conductivity. mechanical strength, in particular excellent HCF strength and LCF strength.
  • the coating according to the invention produced by the process according to the invention from the platinum-aluminum substrate region shown in FIG 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 FIG. 2, the component 10 adjacent 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, a ceramic layer 15 comprises, between the ceramic layer 15 and the outer layer 13 of the platinum-aluminum substrate portion 12, an aluminum oxide intermediate layer 16 is formed.
  • a ceramic layer 15 comprises, between the ceramic layer 15 and the outer layer 13 of the platinum-aluminum substrate portion 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.
  • the 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.
  • aluminum is deposited using a high-activity gas-phase process in an atmosphere of aluminum monohalide, the proportion of aluminum monohalide in the atmosphere being at least 15 vol. % is. Subsequently, the aluminum is diffused at an activity of the aluminum of at least 50 at%, again based on pure nickel, preferably at a temperature of 1040 ° C and a holding time of 330 min.
  • 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. 3 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, 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.
  • the curve 19 shown in FIG. 3 with solid lines corresponds to a component coated according to the invention
  • the curve 20 shown in dashed lines corresponds to a component coated according to the prior art.
  • Fig. 3 it can be seen that at the beginning of the test time, the weight of the coated component according to the invention increases relatively slowly and relatively low, from which it is concluded that the invention coated component oxidation begins relatively slowly.
  • a weight loss compared to the prior art sets relatively late, which provides information that the coating over the prior art long on the component remains, thus flaking of the coating begins relatively late. It follows that, compared to the prior art, a component coated according to the invention has, on the one hand, improved oxidation and corrosion properties and, on the other hand, improved durability.

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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)
EP06015645.2A 2005-08-02 2006-07-27 Composant revetu Ceased EP1754801B1 (fr)

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DE102005036162A DE102005036162A1 (de) 2005-08-02 2005-08-02 Bauteil mit einer Beschichtung

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WO2008145093A3 (fr) * 2007-06-01 2009-04-30 Mtu Aero Engines Gmbh PROCÉDÉ POUR DÉFINIR LE NOMBRE DE PHASES D'UNE COUCHE DE PtAl D'UN COMPOSANT DE TURBINE À GAZ ET PROCÉDÉ DE PRODUCTION D'UNE COUCHE DE PtAl À PHASE UNIQUE SUR UN COMPOSANT DE TURBINE À GAZ
EP1908857A3 (fr) * 2006-10-05 2009-10-14 General Electric Company Procédé de formation d'un revêtement de barrière thermique
WO2010094273A2 (fr) 2009-02-21 2010-08-26 Mtu Aero Engines Gmbh Fabrication d'aubes et disque combinés de turbine avec une couche de protection contre l'oxydation ou la corrosion

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DE102007008278A1 (de) * 2007-02-20 2008-08-21 Mtu Aero Engines Gmbh Beschichtung für Gasturbinenbauteile sowie Verfahren und Vorrichtung zur Bereitstellung einer Beschichtung
DE102009010110B4 (de) * 2009-02-21 2014-08-28 MTU Aero Engines AG Erosionsschutz-Beschichtungssystem für Gasturbinenbauteile
WO2012075425A2 (fr) * 2010-12-03 2012-06-07 Electrolytic Ozone Inc. Pile électrolytique pour la production d'ozone
US8807955B2 (en) * 2011-06-30 2014-08-19 United Technologies Corporation Abrasive airfoil tip
US10539039B2 (en) * 2012-08-14 2020-01-21 Safran Aircraft Engines Method of measuring the temperature reached by a part, in particular a turbine engine part
CA3192359A1 (fr) 2020-08-18 2022-02-24 Enviro Metals, LLC Affinage de metaux
EP4214402A4 (fr) * 2020-09-17 2024-11-27 Applied Materials, Inc. Revêtements protecteurs à l'oxyde d'aluminium sur des composants de turbocompresseur et d'autres composants d'équipement rotatif

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EP0784104B1 (fr) 1995-12-22 2001-05-16 General Electric Company Superalliage à base de nickel ayant un revêtement de platine-aluminure optimisé
US6589668B1 (en) 2000-06-21 2003-07-08 Howmet Research Corporation Graded platinum diffusion aluminide coating

Cited By (5)

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EP1908857A3 (fr) * 2006-10-05 2009-10-14 General Electric Company Procédé de formation d'un revêtement de barrière thermique
WO2008145093A3 (fr) * 2007-06-01 2009-04-30 Mtu Aero Engines Gmbh PROCÉDÉ POUR DÉFINIR LE NOMBRE DE PHASES D'UNE COUCHE DE PtAl D'UN COMPOSANT DE TURBINE À GAZ ET PROCÉDÉ DE PRODUCTION D'UNE COUCHE DE PtAl À PHASE UNIQUE SUR UN COMPOSANT DE TURBINE À GAZ
WO2010094273A2 (fr) 2009-02-21 2010-08-26 Mtu Aero Engines Gmbh Fabrication d'aubes et disque combinés de turbine avec une couche de protection contre l'oxydation ou la corrosion
DE102009010109A1 (de) 2009-02-21 2010-09-23 Mtu Aero Engines Gmbh Herstellung einer Turbinenblisk mit einer Oxikations- bzw. Korrosionsschutzschicht
DE102009010109A8 (de) * 2009-02-21 2011-01-05 Mtu Aero Engines Gmbh Herstellung einer Turbinenblisk mit einer Oxidations- bzw. Korrosionsschutzschicht

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DE102005036162A1 (de) 2007-02-08
EP1754801B1 (fr) 2014-05-14
US20080166589A1 (en) 2008-07-10
US7655321B2 (en) 2010-02-02

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