EP1111091B1 - Verfahren zur Herstellung eines Aluminid-Überzugs mit einem aktiven Element als Beschichtung und Verbindungsschicht und beschichteter Gegenstand - Google Patents

Verfahren zur Herstellung eines Aluminid-Überzugs mit einem aktiven Element als Beschichtung und Verbindungsschicht und beschichteter Gegenstand Download PDF

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Publication number
EP1111091B1
EP1111091B1 EP00311496A EP00311496A EP1111091B1 EP 1111091 B1 EP1111091 B1 EP 1111091B1 EP 00311496 A EP00311496 A EP 00311496A EP 00311496 A EP00311496 A EP 00311496A EP 1111091 B1 EP1111091 B1 EP 1111091B1
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Prior art keywords
coating
aluminide
substrate
overlay
platinum
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EP00311496A
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English (en)
French (fr)
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EP1111091A1 (de
Inventor
Sudhangsu Bose
Walter E. Olson
David N. Duhl
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RTX Corp
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United Technologies Corp
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Priority claimed from US09/735,223 external-priority patent/US20020132132A1/en
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer

Definitions

  • the present invention relates generally to oxidation and corrosion resistant coatings, and relates more particularly to aluminide coatings containing one or more active elements and improved oxidation and corrosion resistance.
  • Overlay coatings are widely used in high temperature and/or corrosive environments, for example in gas turbine engines, as a stand alone coating, e.g., to provide high temperature corrosion and oxidation resistance to the underlying substrate, and also as an adherent bond coat for a subsequently-applied ceramic thermal barrier coatings.
  • a typical overlay coating is an MCr, MCrAl or MCrAlY coating, such as a coating disclosed in commonly-owned U.S. Pat. No. 4,585,481 and Reissue No. 32,121, both to Gupta et al .
  • the M is selected from the group including nickel, cobalt and iron or combinations of these elements.
  • the Y typically indicates yttrium but may also include silicon and/or other active elements such as hafnium.
  • Overlay coatings are generally, although not necessarily, applied by plasma spraying. See, e.g., U.S. Pat. Nos. 4,321,311 and 4,585,481 and Reissue No. 32,121 . Application of overlay coatings by other applications, including but not limited to, electron-beam physical vapor deposition, chemical vapor deposition, cathodic arc and electroplating are also possible. While the bond coat thickness may vary depending upon the particular component and application, the illustrated bond coat typically has a thickness of less than about 5 mils (125 ⁇ m), although thicker or thinner coatings are also used.
  • Aluminide coatings are also used in high temperature and/or corrosive environments, for example in gas turbine engines, as a stand alone coating, e.g., to provide high temperature corrosion and oxidation resistance to the underlying substrate, and as an adherent bond coat for a subsequently-applied ceramic thermal barrier coating.
  • Some aluminide coatings also include one or more noble metals, which enhance erosion and/or corrosion resistance. See, e.g., U.S. Pat. No. 5,856,027 to Murphy .
  • Aluminide coatings, including those containing noble metal(s) are traditionally applied by a pack process or by chemical vapor deposition (CVD).
  • the article to be coated is usually initially electroplated with a noble metal, and is then placed in a pack containing a source of aluminum, an activator, e.g., halide, and inert materials, e.g., alumina.
  • the pack and article are then heated, forming vapors of the aluminum, which reacts with the nickel or cobalt in the article to form the aluminide.
  • the coatings may be further heat treated to obtain desired coating properties.
  • individual generators produce aluminum vapors, and the vapors are conveyed into a chamber to a heated article to be coated where the vapors condense and react with the nickel or cobalt in the article to form the aluminide.
  • U.S. Pat. No. Re 32,121 describes forming an MCrAIY (M including nickel, cobalt or a combination) bond coat by plasma spraying, with the MCrAIY composition including about 0.1 - 0.7 % silicon, and 0.1 - 2 % hafnium.
  • U.S. Pat. No. 4,897,315 describes a plasma sprayed NiCoCrAlY overlay, which is then aluminized to form an aluminide coating on the substrate.
  • U.S. Pat. No. 5,658,614 describes a platinum aluminide (without an MCrAlY) coating formed by electroplating the platinum onto the substrate, and then aluminizing by CVD.
  • a method for improving the corrosion and oxidation resistance of a substrate.
  • the method includes providing a superalloy substrate, and an overlay coating including at least one oxygen active element which is applied onto the substrate by an overlay step. Platinum is applied onto the overlay coating, by electroplating. The overlay coating and metal is then aluminized by chemical vapor deposition. A ceramic thermal barrier coating may also be applied.
  • a coated article is also disclosed.
  • a substrate having an aluminide coating in accordance with the present invention is illustrated by the reference numeral 10.
  • the coating may serve as a stand alone coating, e.g., for high temperature oxidation resistance, or as an adherent bond coat for a subsequently-applied thermal barrier such as a layer of ceramic material, e.g., stabilized zirconia.
  • a ceramic layer is applied over the aluminide to form a thermal barrier.
  • the ceramic layer may be a stabilized zirconia, such as is disclosed in commonly owned U.S. Pat. 4,321,311 to Strangman or Ser. No. 09/164,700 to Maloney both of which are commonly owned with the present invention and are expressly incorporated by reference herein.
  • a substrate 12 is typically composed of nickel, cobalt and /or iron base superalloy material.
  • an overlay coating 14 such as an MCrAI type coating is first applied to the substrate, by low pressure plasma spray and together with one or more oxygen active elements such as hafnium, yttrium and silicon or other oxygen active element. Platinum is then deposited by electroplating, and is aluminized to form an adherent alumina layer 16.
  • the article is also heat treated to provide the coating with desired properties, e.g., improved mechanical properties.
  • the present invention provides coatings having improved properties, e.g., corrosion and oxidation resistance and durability relative to prior coatings. While the invention illustrated below is used with a nickel base, cobalt base or iron base superalloy material, the invention is not limited to use with these materials.
  • Typical compositions of such alloys are shown in Table 1.
  • Exemplary U.S. Patents describing columnar and single crystal and directionally solidified alloys include 4,209,348 ; 4,643,782 ; 4,717,432 ; 4,719,080 and 5,068,084 , each of which is expressly incorporated by reference herein.
  • Cooling holes which may be positioned on one or more portions of a turbine blade, may be provided for flowing cooling air over the specific portions of the airfoil during operation, as is known generally in the art.
  • TABLE 1 COMPOSITION OF COLUMNAR AND SINGLE CRYSTAL ALLOYS Alloy Type Ni Co Cr Al Mo Ta W Re Hf Ti Nb PWA 1422 DS Bal.
  • Rene N4 and CMSX-2 are described in the prior art.
  • the active element(s) is applied by a conventional overlay process, and may or may not contain other elements, e.g., as part of an MCr or MCrAI overlay coating.
  • an overlay coating such as an MCrAI is applied to the substrate surface by low pressure plasma spray.
  • M indicates nickel, cobalt, iron and mixtures thereof.
  • the bond coat also includes at least one oxygen active element, e.g., yttrium, hafnium, silicon or others.
  • the present invention includes an overlay coating having a thickness of between about 1 - 5 mils (0.001 - 0.005 inches, (25.4-127 ⁇ m).
  • the overlay coating (described further in an example below) according to the invention which we have used successfully is a NiCoCrAl coating with added Y, Hf and/or Si.
  • the coating is composed in weight percentage of about 5 - 40 Cr, 8 - 35 Al, up to 2 Y, 0.1 - 7 Si, 0.1 - 5.5 Hf, balance Ni and/or Co.
  • Platinum is then deposited on the MCrAI coating. We believe that the final coating should contain in weight percent 10 - 11 Pt as described below we have obtained good results. Platinum is deposited by electroplating, in a known manner. Plating the platinum to a thickness of about 0.05 - 0.15 mils (1.3-3.8 ⁇ m) shood provide a final coating with the above-desired transition metal content. Plating processes are known generally and are not described here in detail.
  • a coating gas has a composition including some amount, in vol. % of a carrier gas, such as hydrogen, and an amount, in vol. %, of an aluminum containing gas.
  • the coating gas may be formed by passing a carrier gas over a source of aluminum. The above process is adjusted as desired to provide a given quantity of aluminum on the part surface.
  • the coating gas is then impinged upon the heated substrate, at a given delivery rate, with the substrate typically being heated to between about 1800 - 2200 F (982 - 1204°C) and preferably about 1950 - 2000F (1065 - 1093°C)
  • the coated part is diffusion heat treated.
  • the diffusion heat treatment includes heating the component to a temperature of about 1975 F (1079°C) for a sufficient time, of about 3 hours, followed by a precipitation heat treatment, at about 1600 °F (871°C) for about 16 hours.
  • a resulting coating is illustrated in FIG. 1 , which includes a subsequently applied, columnar grain, ceramic thermal barrier layer.
  • coatings in accordance with the present invention may be employed to provide stand alone coatings or bond coats for subsequently-applied ceramic thermal barrier coating.
  • Typical ceramics are zirconia based, and may be partially or fully stabilized with additions of yttria or other appropriate stabilizer.
  • Exemplary ceramic coatings composed of yttria stabilized zirconia (YSZ) are described, for example, in commonly-owned U.S. Pat. Nos. 4,321,311 , 5,262,245 .
  • the ceramic may be applied by EB-PVD, by plasma spray or by another suitable method.
  • Samples were prepared using superalloy substrates in accordance with preferred embodiments and some were also coated with a standard, zirconia based columnar ceramic thermal barrier coating.
  • the overlay coating as described above was applied by low pressure plasma spray, and then plated with platinum in a known manner.
  • the samples were aluminized using a coating gas included about 80 vol. % of a carrier gas, such as hydrogen, and about 20 vol. %, of an aluminum containing gas, in this case AlCl 3 .
  • the coating gas was formed by passing HCI over a source of aluminum at about 600 C.
  • the coating gas was impinged upon the heated substrate, at a delivery rate of about 224 standard cubic feet per minute, with the substrate heated to a nominal temperature of between about 1950-2000 F (1065-1093°C).
  • Some of the samples were then coated with a ceramic thermal barrier coating composed of yttria stabilized zirconia, as taught for example in the above referenced '311 patent to Strangman, while other samples were tested
  • Coated articles in accordance with the present invention have been tested in a burner rig apparatus. Testing indicated that the present invention coatings, which tests included samples having a subsequently applied thermal insulating layer, are about 2 - 3 times more durable than current TBC's. The inventive coated articles were also tested as stand alone coatings, e.g., no overlying ceramic layer, and also demonstrate improved protection and durability.
  • the samples were tested in high temperature burner rigs.
  • the test cycles comprised 117 minute exposure at 2150 degree F (1176°C) followed by 3 minute air cooling per cycle together with standard platinum aluminides.
  • the samples prepared in accordance with the present method exhibited improved lives over the samples including the standard aluminides by a factor of about 2.5.
  • composition of the final coating is, in weight percent, 10 - 11 Pt, 2.6 - 4.2 Si, 13.4 - 13.6 Al, 3.9 - 5.3 Hf, remainder Ni, Co, and Cr.
  • the present invention provides significant advantages over prior processes.
  • the improved process enables the production of active element containing aluminide coatings having significantly more consistent compositions, and thus significantly more consistent properties and improved durability.
  • the quality of the resulting coatings are thus similarly improved.

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

Claims (4)

  1. Verfahren zur Verbesserung der Korrosions- und Oxidationsbeständigkeit eines Substrats, folgende Schritte aufweisend:
    Bereitstellen eines Superlegierungs-Substrats (44);
    Auftragen einer MCrAI-Deckschicht-Beschichtung, die mindestens ein Sauerstoffaktives Element enthält, auf das Substrat durch Niederdruckplasmasprit- zen;
    Elektroplattieren von Platin auf die Deckschicht-Beschichtung (48);
    Aluminieren der MCrAI-Deckschicht-Beschichtung und des Platins (50) durch chemische Dampfabscheidung bei einer Temperatur von zwischen 1950 bis 2000 °F (1065 bis 1093 °C), um eine Aluminid-Beschichtung zu bilden;
    Diffusionswärmebehandeln; und
    Ausscheidungswärmebehandeln,
    dadurch gekennzeichnet, dass:
    die Deckschicht-Beschichtung, in Gew.%, besteht aus 5-40 Cr, 8-35 Al, bis zu 2 Y, 0,1-7 Si, 0,1-5,5 Hf, Rest Ni und/oder Co;
    die Diffusionswärmebehandlung bei einer Temperatur von 1975 °F (1079 °C) 3 Stunden lang stattfmdet;
    die Ausscheidungswärmebehandlung bei 1600 °F (871 °C) 16 Stunden lang stattfindet;
    die Deckschicht-Beschichtung in einer Dicke von 1-5 mil (25,4-127 µm) aufgetragen wird;
    das Platin in einer Dicke von 0,05-0,15 mil (1,3-3,8 µm) elektroplattiert wird; und
    die Aluminid-Beschichtung eine Sollzusammensetzung, in Gew.%, von 10-11 Pt, 2,6-4,2 Si, 13,4-13,6 Al, 3,9-5,3 Hf, Rest Ni, Co, und Cr hat.
  2. Verfahren wie in Anspruch 1 beansprucht, außerdem aufweisend den Schritt des Abscheidens einer thermisch isolierenden Keramik auf dem Aluminid (54).
  3. Verfahren wie in Anspruch 2 beansprucht, bei dem die Keramikbeschichtung aus einem stabilisierten Zirconiumdioxid besteht.
  4. Verfahren wie in Anspruch 3 beansprucht, bei dem das Zirconiumdioxid durch Yttriumoxid oder durch Gadoliniumoxid stabilisiert wird.
EP00311496A 1999-12-21 2000-12-20 Verfahren zur Herstellung eines Aluminid-Überzugs mit einem aktiven Element als Beschichtung und Verbindungsschicht und beschichteter Gegenstand Expired - Lifetime EP1111091B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US17282499P 1999-12-21 1999-12-21
US172824P 1999-12-21
US09/735,223 US20020132132A1 (en) 2000-12-12 2000-12-12 Method of forming an active-element containing aluminide as stand alone coating and as bond coat and coated article

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EP1111091A1 EP1111091A1 (de) 2001-06-27
EP1111091B1 true EP1111091B1 (de) 2010-06-23

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JP (1) JP2002115081A (de)
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Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1327702A1 (de) 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd MCrAlY-Haftschicht und Verfahren zur Herstellung einer MCrAlY-Haftschichtbeschichtung
US6861157B2 (en) * 2002-03-18 2005-03-01 General Electric Company Article for high temperature service and method for manufacture
US6746783B2 (en) * 2002-06-27 2004-06-08 General Electric Company High-temperature articles and method for making
RU2219273C1 (ru) * 2002-09-27 2003-12-20 Государственное учреждение Институт металлургии Уральского отделения РАН Хром-кобальт-иттриевый алюминид и способ его получения
EP1428982B1 (de) * 2002-12-06 2009-02-04 ALSTOM Technology Ltd Verfahren zur selektiven Abscheidung einer MCrAlY-Beschichtung
US7273662B2 (en) 2003-05-16 2007-09-25 Iowa State University Research Foundation, Inc. High-temperature coatings with Pt metal modified γ-Ni+γ′-Ni3Al alloy compositions
EP1491659B1 (de) * 2003-06-26 2006-06-07 ALSTOM Technology Ltd Verfahren für das Auftragen eines mehrschichtigen Systems
US7153586B2 (en) 2003-08-01 2006-12-26 Vapor Technologies, Inc. Article with scandium compound decorative coating
US20050035086A1 (en) * 2003-08-11 2005-02-17 Chen Keng Nam Upgrading aluminide coating on used turbine engine component
US7927722B2 (en) * 2004-07-30 2011-04-19 United Technologies Corporation Dispersion strengthened rare earth stabilized zirconia
US7229701B2 (en) * 2004-08-26 2007-06-12 Honeywell International, Inc. Chromium and active elements modified platinum aluminide coatings
US20060141283A1 (en) * 2004-12-29 2006-06-29 Honeywell International, Inc. Low cost inovative diffused MCrAIY coatings
US20070026205A1 (en) 2005-08-01 2007-02-01 Vapor Technologies Inc. Article having patterned decorative coating
CA2564539C (en) * 2005-11-14 2014-05-06 Sulzer Metco Coatings B.V. A method for coating of a base body with a platinum modified aluminide ptmal by means of a physical deposition out of the gas phase
EP1795623A1 (de) * 2005-11-14 2007-06-13 Sulzer Metco AG Verfahren zum Beschichten eines Grundkörpers mit platinmodifiziertem Aluminid sowie Werkstück
US7875370B2 (en) * 2006-08-18 2011-01-25 United Technologies Corporation Thermal barrier coating with a plasma spray top layer
US7727318B2 (en) * 2007-01-09 2010-06-01 General Electric Company Metal alloy compositions and articles comprising the same
US7931759B2 (en) 2007-01-09 2011-04-26 General Electric Company Metal alloy compositions and articles comprising the same
US7846243B2 (en) 2007-01-09 2010-12-07 General Electric Company Metal alloy compositions and articles comprising the same
US20090035485A1 (en) * 2007-08-02 2009-02-05 United Technologies Corporation Method for forming active-element aluminide diffusion coatings
US8821654B2 (en) 2008-07-15 2014-09-02 Iowa State University Research Foundation, Inc. Pt metal modified γ-Ni+γ′-Ni3Al alloy compositions for high temperature degradation resistant structural alloys
DE102009010026A1 (de) * 2009-02-21 2010-08-26 Mtu Aero Engines Gmbh Bauteil für eine Strömungsmaschine
US20130115072A1 (en) * 2011-11-09 2013-05-09 General Electric Company Alloys for bond coatings and articles incorporating the same
JP5857794B2 (ja) * 2012-02-27 2016-02-10 株式会社Ihi 拡散層付き金属材料ならびにその製造方法
US9663870B2 (en) * 2013-11-13 2017-05-30 Applied Materials, Inc. High purity metallic top coat for semiconductor manufacturing components
TWI642552B (zh) * 2014-09-12 2018-12-01 香港浸會大學 經藍寶石薄膜塗覆之可撓基板
CN112458351B (zh) * 2020-10-22 2021-10-15 中国人民解放军陆军装甲兵学院 高抗压强度的镍钴基高温合金
DE112022002426T5 (de) * 2021-04-26 2024-02-22 Agilent Technologies, Inc. Mehrlagige Beschichtung für Interface-Konen
CN114672859B (zh) * 2022-03-11 2024-05-17 沈阳梅特科航空科技有限公司 一种可作为热障涂层粘结层的铂改性铝化物涂层及其制备工艺

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE759275A (fr) * 1969-12-05 1971-04-30 Deutsche Edelstahlwerke Ag Procede d'application de couches protectrices diffusees sur despieces en alliage a base de cobalt
US3979273A (en) * 1975-05-27 1976-09-07 United Technologies Corporation Method of forming aluminide coatings on nickel-, cobalt-, and iron-base alloys
USRE32121E (en) 1981-08-05 1986-04-22 United Technologies Corporation Overlay coatings for superalloys
WO1985003460A1 (en) 1984-02-13 1985-08-15 Schmitt Jerome J Iii Method and apparatus for the gas jet deposition of conducting and dielectric thin solid films and products produced thereby
US4897315A (en) 1985-10-15 1990-01-30 United Technologies Corporation Yttrium enriched aluminide coating for superalloys
FR2638174B1 (fr) * 1988-10-26 1991-01-18 Onera (Off Nat Aerospatiale) Procede de protection de surface de pieces metalliques contre la corrosion a temperature elevee, et piece traitee par ce procede
US4933239A (en) * 1989-03-06 1990-06-12 United Technologies Corporation Aluminide coating for superalloys
GB9218858D0 (en) * 1992-09-05 1992-10-21 Rolls Royce Plc High temperature corrosion resistant composite coatings
US5427866A (en) * 1994-03-28 1995-06-27 General Electric Company Platinum, rhodium, or palladium protective coatings in thermal barrier coating systems
US5658614A (en) 1994-10-28 1997-08-19 Howmet Research Corporation Platinum aluminide CVD coating method
US6129991A (en) * 1994-10-28 2000-10-10 Howmet Research Corporation Aluminide/MCrAlY coating system for superalloys
US5716720A (en) * 1995-03-21 1998-02-10 Howmet Corporation Thermal barrier coating system with intermediate phase bondcoat
GB2319783B (en) * 1996-11-30 2001-08-29 Chromalloy Uk Ltd A thermal barrier coating for a superalloy article and a method of application thereof

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JP2002115081A (ja) 2002-04-19
DE60044574D1 (de) 2010-08-05
EP1111091A1 (de) 2001-06-27
SG98436A1 (en) 2003-09-19

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