EP1908857A2 - Procédé de formation d'un revêtement de barrière thermique - Google Patents

Procédé de formation d'un revêtement de barrière thermique Download PDF

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Publication number
EP1908857A2
EP1908857A2 EP07117636A EP07117636A EP1908857A2 EP 1908857 A2 EP1908857 A2 EP 1908857A2 EP 07117636 A EP07117636 A EP 07117636A EP 07117636 A EP07117636 A EP 07117636A EP 1908857 A2 EP1908857 A2 EP 1908857A2
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EP
European Patent Office
Prior art keywords
overlay coating
predominantly
nickel aluminide
coating
coated substrate
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.)
Withdrawn
Application number
EP07117636A
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German (de)
English (en)
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EP1908857A3 (fr
Inventor
Ramgopal Darolia
Brian Thomas Hazel
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General Electric Co
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General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP1908857A2 publication Critical patent/EP1908857A2/fr
Publication of EP1908857A3 publication Critical patent/EP1908857A3/fr
Withdrawn legal-status Critical Current

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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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment

Definitions

  • the technology disclosed herein relates generally to coatings of the type used to protect components exposed to high temperature environments, such as the hostile thermal environment of a gas turbine engine.
  • TBC thermal barrier coating
  • thermal barrier coatings must have low thermal conductivity, strongly adhere to the component, and remain adherent throughout many heating and cooling cycles. The latter requirement is particularly demanding due to the different coefficients of thermal expansion between materials having low thermal conductivity and superalloy materials typically used to form turbine engine components.
  • TBC systems capable of satisfying the above requirements have generally required a bond coat, such as diffusion coatings (i.e., diffusion aluminides and platinum aluminides) and overlay coatings (i.e., MCrAlX, where M is iron, cobalt and/or nickel and X is yttrium or other rare earth element).
  • the ceramic layer is typically deposited by air plasma spraying (APS), low pressure plasma spraying (LPPS), or a physical vapor deposition (PVD) technique, such as electron beam physical vapor deposition (EBPVD), which yields a strain-tolerant columnar grain structure.
  • APS air plasma spraying
  • LPPS low pressure plasma spraying
  • PVD physical vapor deposition
  • EBPVD electron beam physical vapor deposition
  • the aluminum content of the above-noted bond coat materials provides for the slow growth of a strong adherent continuous aluminum oxide layer (alumina scale) at elevated temperatures.
  • This thermally grown oxide (TGO) protects the bond coat from oxidation and hot corrosion, and chemically bonds the ceramic layer to the bond coat.
  • TGO thermally grown oxide
  • a thermal expansion mismatch exists between the metallic bond coat, alumina scale, and ceramic layer. Tensile stresses generated by this mismatch gradually increase over time to the point where spallation can occur at the interface between the bond coat and alumina scale or the interface between the alumina scale and ceramic layer.
  • bond coat materials are particularly alloyed to be oxidation-resistant
  • the surface oxidation and interdiffusion (with the substrate) that occurs over time at elevated temperatures gradually depletes aluminum from the bond coat.
  • the level of aluminum within the bond coat can become sufficiently depleted to prevent further slow growth of the protective alumina scale and to allow for the more rapid growth of nonprotective oxides, the result of which again is spallation of the ceramic layer.
  • the alumina scale includes predominately meta-stable alumina (gamma- and theta-) with little or no alpha-alumina.
  • the bond-coated article Prior to deposition of the ceramic layer, the bond-coated article is usually preheated to about 1700 to about 1900 °F (about 927 to about 1038 °C). This preheat process is also not favorable to alpha-alumina formation.
  • the meta-stable alumina phases transform to the more stable alpha-alumina over time. However, undesirable volumetric changes accompany the transformation between alumina phases. Additionally, the meta-stable phases generally exhibit high growth rate, poor adherence, and intrinsic porosity.
  • bond coats formed of an overlay i.e., not diffusion
  • predominantly beta ( ⁇ ) phase nickel aluminide (NiAl) intermetallic have been proposed for use in high temperature applications.
  • overlay environmental coatings and bond coats comprising predominantly gamma prime-phase nickel aluminide (Ni 3 Al) are under investigation.
  • Improvement in performance of the coating system is a continuing requirement in order for components to survive the increasingly severe operating conditions in high performance gas turbine engines. Therefore, it is desirable to provide coating systems and methods for enhancing performance, particularly at the interface between the bond coat and the ceramic layer.
  • exemplary embodiments which provide methods for coating articles.
  • the disclosed methods provide coatings having increased oxidation resistance and reduced spallation of the ceramic layer, if present, by promoting formation of stable ⁇ -alumina scale on a protective overlay coating.
  • a method includes providing a coated superalloy substrate having an overlay coating on at least one surface, and subjecting the coated substrate to predetermined conditions to grow an aluminum oxide scale on the overlay coating, wherein the aluminum oxide comprises predominantly alpha phase alumina.
  • the overlay coating is selected from the group consisting of a nickel aluminide intermetallic predominantly of beta phase, a nickel aluminide intermetallic predominantly of beta plus gamma prime phases, a nickel aluminide intermetallic predominantly of gamma plus gamma prime phases, and a nickel aluminide intermetallic predominantly of gamma prime phase.
  • a method in another exemplary embodiment, includes providing a coated superalloy substrate with an overlay coating on at least one surface.
  • the overlay coating is selected from the group consisting oF a nickel aluminide intermetallic predominantly of beta phase, a nickel aluminide intermetallic predominantly of beta plus gamma prime phases, a nickel aluminide intermetallic predominantly of gamma plus gamma prime phases, and a nickel aluminide intermetallic predominantly of gamma prime phase.
  • the selected overlay coating is physically modified by milling, honing, or grit blasting.
  • the coated substrate is heated in a vacuum chamber at a temperature of at least about 2000 °F (1093 °C) to about 2100 °F (1149 °C), for at least about 2 to about 8 hours, under a vacuum of from 10 -3 to about 10 -6 Torr to grow a predominantly alpha phase aluminum oxide scale on the selected overlay coating.
  • the coated substrate is then pre-heated in a deposition chamber at a temperature of from about 1700 °F (927 °C) to about 2000 °F (1093 °C) for about 10 to about 30 minutes. Finally, a thermally insulating ceramic layer is deposited on the overlay coating.
  • the selected overlay coating may be deposited by a physical vapor deposition technique selected from the group consisting of magnetron sputtering, electron beam physical vapor deposition, jet vapor deposition, cathodic arc deposition and plasma spraying.
  • FIG. 1 shows an exemplary component, such as a turbine blade 10, that is operable within environments characterized by relatively high temperatures, and are therefore subjected to severe thermal stresses and thermal cycling.
  • exemplary components include, but are not limited to, turbine nozzles and blades, shrouds, combustor liners, and augmentor hardware of gas turbine engines.
  • the blade 10 generally includes an airfoil 12 against which hot combustion gases are directed during operation of the gas turbine engine, and whose surface is therefore subjected to severe attack by oxidation, corrosion, and erosion.
  • the exemplary airfoil 12 is anchored to a turbine disk (not shown) with a dovetail 14 formed on a root section 16 of the blade 10.
  • Cooling passages 18 may be present in the airfoil 12 through which bleed air is forced to transfer heat from the blade 10. While reference is made herein to a particular component, i.e., blade 10, the teachings herein are generally applicable to any component on which an environmental or thermal barrier coating system may be used to protect the component from its environment.
  • the exemplary thermal barrier coating system 20 illustrated as a longitudinal section through airfoil 12, which serves as substrate 22.
  • the exemplary coating system 20 includes a protective layer 24, which overlies at least a surface of substrate 22.
  • a ceramic layer 26 overlies and contacts the protective layer 24.
  • the protective layer 24 is termed an "environmental coating.”
  • the protective layer 24 is termed a "bond coat.”
  • deposition of the protective layer 24 may result in virtually no diffusion between the overlay coating and substrate 22.
  • a thin diffusion zone 30 may develop.
  • a minimal thickness of the diffusion zone in the overlay coating reduces the amount of substrate material that must be removed during refurbishment of the coating system 20, as compared to a diffusion-type bond coat.
  • the substrate 22 is preferably a high-temperature material, such as an iron, nickel, or cobalt-base superalloy.
  • exemplary materials include Rene N4, Rene N5, Rene N6. These superalloys are presented as examples, and the teachings disclosed herein are not limited for use with substrates of these materials.
  • the ceramic layer 26 may be an yttria-stabilized zirconia (YSZ), which may be about 6 to about 8 weight percent yttria, although other ceramic materials could be used, such as yttria, non-stabilized zirconia, or zirconia stabilized by ceria (CeO 2 ), magnesia (MgO), scandia (Sc 2 O 3 ), or other oxides.
  • YSZ yttria-stabilized zirconia
  • the ceramic layer 26 is deposited to a thickness that is sufficient to provide the required thermal protection for the underlying substrate 22, generally on the order of about 125 to about 300 micrometers.
  • the ceramic layer 26 may be deposited by physical vapor deposition (PVD) to attain a strain-tolerant columnar grain structure, although other deposition techniques could be used.
  • PVD physical vapor deposition
  • the protective layer 24 may be an overlay coating comprising a nickel aluminide intermetallic.
  • the nickel aluminide intermetallic may be predominately of beta phase, beta- plus gamma-prime phases, gamma-prime phase, and gamma plus gamma-prime phases, each of which may include further alloying additions such as chromium, zirconium, hafnium, silicon, tantalum, platinum, yttrium, lanthanum, calcium, cobalt, rhenium, singly or in combination.
  • the protective layer 24 includes a continuous adherent thermally grown oxide (TGO) or alumina scale 28 formed in situ on the protective layer 24 that adheres the ceramic layer 26.
  • the TGO increases the adherence of the ceramic layer 26, and reduces diffusion of oxygen through the TGO, thereby reducing the oxidation rate.
  • the alumina may comprise meta-stable alumina (i.e., theta- or gamma-alumina) or stable alumina (i.e., alpha-alumina).
  • the alumina phase that is initially formed is dependent on temperature, time, exposure environment, specimen composition and surface finish.
  • the methods disclosed herein provide for controlled growth of the alpha-alumina scale 28 on the surface of the protective layer 24 to resist spallation, cracking or other TBC failure, particularly at the bond coat/ceramic layer interface.
  • alumina scale 28 on the disclosed overlay coatings (i.e., protective layer 24) in a manner that is conducive to formation of stable ⁇ -alumina rather than the meta-stable alumina (i.e., gamma-, and theta-alumina).
  • a surface of the substrate 22 is coated with a protective layer 24.
  • the protective layer 24 may be an overlay coating predominantly of beta-phase intermetallic NiAl.
  • U.S. Patent No. 6,682,827 discloses a beta-phase NiAl intermetallic overlay coating containing nickel and, in atomic percent, about 30% to about 60% aluminum and about 1 % to about 12% platinum-group metal.
  • the overlay coating consists essentially of intermetallic phases of beta-phase NiAl and platinum-group intermetallic phases.
  • Other disclosed overlay coatings include an overlay coating consisting essentially of, in atomic percent, 30% to 60% aluminum, about 5% to about 12% platinum, about 2% to about 15% chromium, about 0.1% to about 1.2% zirconium, the balance essentially nickel.
  • 6,579,627 discloses a predominantly beta phase intermetallic NiAl overlay coating comprising nickel, from about 20 to about 35 weight percent aluminum, and at least two modifying elements (i.e., zirconium, hafnium, yttrium, and silicon).
  • U.S. Patent No. 6,153,313 discloses a predominantly beta phase NiAl intermetallic overlay coating consisting of 30 to 60 atomic percent aluminum, at least one of chromium, titanium, hafnium, and optionally tantalum, silicon, gallium, zirconium, calcium, iron, and yttrium, the balance nickel and impurities.
  • 6,291,084 discloses a beta-phase NiAl intermetallic overlay coating including 30% to 60% aluminum, 2% to 15% chromium, 0.1 % to 1.2% zirconium, and the balance essentially nickel.
  • U.S. Patent No. 6,255,001 discloses a bond coat comprising a NiAl alloy of predominately the beta phase, containing at least 0.2 atomic percent zirconium, and has an average grain size of less than 3 micrometers.
  • the protective layer 24 may be an overlay coating predominantly of gamma prime-phase intermetallic nickel aluminide (Ni 3 Al).
  • the overlay coating may contain nickel aluminide intermetallic predominantly of the gamma prime phase and at least one platinum group metal.
  • the exemplary overlay coating may further contain chromium.
  • the exemplary overlay coating may contain at least one reactive element.
  • Other exemplary overlay coatings predominantly of gamma prime-phase intermetallic nickel aluminide (Ni 3 Al) are disclosed in U.S. Publication No. 2006/0093850 .
  • the overlay coating may contain an as-deposited composition comprising, by weight, at least 6% to about 15% aluminum, about 2% to about 5% chromium, optionally up to 4% of at least one reactive element, optionally up to 2% silicon, optionally up to 60% of at least one platinum group metal, and the balance essentially nickel and incidental impurities.
  • the protective layer 24 may be an overlay coating predominantly of beta- plus gamma prime-phase intermetallic nickel aluminide.
  • an exemplary overlay coating comprises, by weight, at least 14% aluminum.
  • An exemplary overlay coating further comprises up to about 4 weight percent of a reactive element such as zirconium, hafnium, yttrium, and cerium.
  • about 10 to about 85 volume percent of the coating consists of the gamma-prime nickel aluminide intermetallic phase, and the balance of the coating consists of the beta nickel aluminide intermetallic phase.
  • the protective layer 24 may be an overlay coating predominantly of gamma- plus gamma prime-phase intermetallic nickel aluminide.
  • the protective layer 24 may be an overlay coating predominantly of gamma- plus gamma prime-phase intermetallic nickel aluminide.
  • U.S. Publication No. 2004/0229075 discloses overlay coatings containing, in atomic %, less than 23% aluminum, 10 to 60% platinum, and 0.3 to 2% of a reactive element.
  • the coated substrate is subjected to controlled environmental conditions conducive to formation of the alpha- phase for the alumina scale 28.
  • the coated substrate 22 is pre-oxidized, in a coating deposition chamber, at an elevated temperature (as compared to prior TBC deposition processes), and for a longer duration (as compared to prior TBC deposition processes).
  • the coated substrate may be pre-oxidized in the chamber at temperatures around 2000 °F for about 2 to about 8 hours to achieve a controlled TGO comprising predominantly alpha-alumina scale.
  • the applied temperature may range from greater than about 1900 °F (1038 °C)to about 2200 °F (1204 °C).
  • the applied temperature may range from about 2000 °F (1093 °C) to about 2150 °F (1178 °C).
  • bond-coated articles are pre-heated to about 1700 °F (927 °C) to about 2000 °F (1093 °C) for about 10 minutes to about 30 minutes in preparation for reception of the ceramic layer.
  • these prior conditions are not conducive to initial alpha-alumina formation on the surface of the protective layer 24.
  • alpha-alumina avoids the volumetric changes that would occur during the pre-heating process if the alumina scale were predominantly a meta-stable form. Additionally, alpha-alumina has the lowest diffusivity of oxygen among the various forms of aluminas, and consequently the slowest growth rate of the oxide scale.
  • the coated substrate 22 is pre-oxidized in a vacuum furnace at the temperature and time sufficient to provide the desired alpha alumina scale.
  • the pre-oxidizing treatment includes about two to about eight hours or an intervening interval, at temperatures from about at least 1900 °F (1038 °C) to about 2150 °F (1178 °C).
  • the vacuum furnace is operated at from about 10 -3 to about 10 -6 Torr.
  • the pre-oxidizing treatment may occur in an atmosphere of air, oxygen, argon, or hydrogen gas containing oxygen.
  • the applied temperature may range from greater than about 1900 °F (1038 °C) to about 2200 °F (1204 °C).
  • the applied temperature may range from about 2000 °F (1093 °C) to at least about 2150 °F (1178 °C).
  • the temperature, pressure, time and atmospheric conditions are chosen for the particular bond coat/substrate combination in order to maximize alpha alumina formation.
  • the coated substrate undergoes a surface preparation prior to the pre-oxidation of the applied protective layer.
  • the surface treatment modifies at least a portion of the overlay coating for later reception of the thermally insulating ceramic layer 26.
  • the surface treatment may include, for example, chemical milling, chemical milling plus vapor honing, grit blasting, and the like.
  • a ceramic layer 26 may be applied to the coated substrate. If the pre-oxidation treatment occurred in a vacuum furnace or other chamber, the coated substrate is then moved to the coating deposition chamber for application of the ceramic layer 26.
  • the pre-oxidized, coated substrate is pre-heated at temperatures from about 1800 °F (982 °C) to about 1900 °F (1038 °C) for about 10 to about 30 minutes before receiving the thermally insulating ceramic barrier coat. Since the coated substrate has been pre-oxidized to provide a predominantly stable alpha-alumina scale, volumetric and other metallurgical transformations are minimized during the pre-heat cycle.
  • Furnace cycle test specimens of 1 inch diameter x 0.125 inch thick (24.5 mm x 3.175 mm) comprising Rene N5 superalloy substrate were coated with a predominantly beta phase-containing overlay coating by an ion plasma deposition method.
  • the nominal composition of the coating after deposition, in wt %, was 20 -24 % Al, 5-6 % Cr, about 0.5 - 1 % Zr, with the balance being Ni.
  • test specimens were subjected to various heat treat and pre-oxidation conditions as shown in Table 1.
  • a 7wt% Y 2 O 3 containing zirconia (YSZ) thermal barrier coating was applied by EB-PVD to a thickness of about 5 mil (127 microns).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
  • Physical Vapour Deposition (AREA)
EP07117636A 2006-10-05 2007-10-01 Procédé de formation d'un revêtement de barrière thermique Withdrawn EP1908857A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US54360906A 2006-10-05 2006-10-05

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EP1908857A2 true EP1908857A2 (fr) 2008-04-09
EP1908857A3 EP1908857A3 (fr) 2009-10-14

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EP (1) EP1908857A3 (fr)
JP (1) JP2008095191A (fr)
BR (1) BRPI0705144A (fr)
CA (1) CA2604570A1 (fr)
SG (2) SG141412A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2365104A1 (fr) * 2010-03-08 2011-09-14 United Technologies Corporation Procédé pour appliquer un revêtement barrière thermique
EP2365107A1 (fr) * 2010-03-04 2011-09-14 United Technologies Corporation Article revêtu et son procédé de revêtement
WO2013171547A1 (fr) 2012-05-16 2013-11-21 Babcock & Wilcox Vølund A/S Échangeur de chaleur présentant une résistance accrue à la corrosion
US9181814B2 (en) 2010-11-24 2015-11-10 United Technology Corporation Turbine engine compressor stator
US9581042B2 (en) 2012-10-30 2017-02-28 United Technologies Corporation Composite article having metal-containing layer with phase-specific seed particles and method therefor
CN110573658A (zh) * 2017-03-30 2019-12-13 赛峰集团 由超合金制成的涡轮部件及其制造方法
WO2020180325A1 (fr) * 2019-03-07 2020-09-10 Oerlikon Metco (Us) Inc. Matériaux de couche d'accrochage avancés pour des tbc présentant une résistance améliorée à la fatigue sous des variations cycliques de température et à la sulfuration

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2715958A1 (fr) * 2009-10-12 2011-04-12 General Electric Company Procede de realisation de preparation de revetement, preparation de revetement resultante, et revetement des elements connexe
FR3071272B1 (fr) * 2017-09-21 2019-09-20 Safran Piece de turbine en superalliage comprenant du rhenium et/ou du ruthenium et procede de fabrication associe

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0733723A1 (fr) * 1995-03-21 1996-09-25 Howmet Corporation Revêtement de barrière thermique
EP1167575A2 (fr) * 2000-06-30 2002-01-02 General Electric Company Revêtement et Systèmes de revêtement à base d'aluminure de nickel
EP1273681A2 (fr) * 2001-07-06 2003-01-08 General Electric Company Procédé pour améliorer la durée de vie d'un revêtement de barrière thermique d'une couche de liaison monophase d'aluminure de platine par traitement de préoxydation
EP1754801A2 (fr) * 2005-08-02 2007-02-21 MTU Aero Engines GmbH Composant revetu

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0733723A1 (fr) * 1995-03-21 1996-09-25 Howmet Corporation Revêtement de barrière thermique
EP1167575A2 (fr) * 2000-06-30 2002-01-02 General Electric Company Revêtement et Systèmes de revêtement à base d'aluminure de nickel
EP1273681A2 (fr) * 2001-07-06 2003-01-08 General Electric Company Procédé pour améliorer la durée de vie d'un revêtement de barrière thermique d'une couche de liaison monophase d'aluminure de platine par traitement de préoxydation
EP1754801A2 (fr) * 2005-08-02 2007-02-21 MTU Aero Engines GmbH Composant revetu

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2365107A1 (fr) * 2010-03-04 2011-09-14 United Technologies Corporation Article revêtu et son procédé de revêtement
US9315905B2 (en) 2010-03-04 2016-04-19 United Technologies Corporation Coated article and coating process therefor
EP2365104A1 (fr) * 2010-03-08 2011-09-14 United Technologies Corporation Procédé pour appliquer un revêtement barrière thermique
US8481117B2 (en) 2010-03-08 2013-07-09 United Technologies Corporation Method for applying a thermal barrier coating
US9181814B2 (en) 2010-11-24 2015-11-10 United Technology Corporation Turbine engine compressor stator
WO2013171547A1 (fr) 2012-05-16 2013-11-21 Babcock & Wilcox Vølund A/S Échangeur de chaleur présentant une résistance accrue à la corrosion
US9581042B2 (en) 2012-10-30 2017-02-28 United Technologies Corporation Composite article having metal-containing layer with phase-specific seed particles and method therefor
CN110573658A (zh) * 2017-03-30 2019-12-13 赛峰集团 由超合金制成的涡轮部件及其制造方法
WO2020180325A1 (fr) * 2019-03-07 2020-09-10 Oerlikon Metco (Us) Inc. Matériaux de couche d'accrochage avancés pour des tbc présentant une résistance améliorée à la fatigue sous des variations cycliques de température et à la sulfuration

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Publication number Publication date
BRPI0705144A (pt) 2008-10-21
SG161232A1 (en) 2010-05-27
JP2008095191A (ja) 2008-04-24
CA2604570A1 (fr) 2008-04-05
EP1908857A3 (fr) 2009-10-14
SG141412A1 (en) 2008-04-28

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