EP2149623A2 - Revêtements de barrière thermique et leurs procédés de production - Google Patents

Revêtements de barrière thermique et leurs procédés de production Download PDF

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Publication number
EP2149623A2
EP2149623A2 EP09161428A EP09161428A EP2149623A2 EP 2149623 A2 EP2149623 A2 EP 2149623A2 EP 09161428 A EP09161428 A EP 09161428A EP 09161428 A EP09161428 A EP 09161428A EP 2149623 A2 EP2149623 A2 EP 2149623A2
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EP
European Patent Office
Prior art keywords
coating
thermal barrier
barrier coating
ceramic
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Withdrawn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
EP09161428A
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German (de)
English (en)
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EP2149623A3 (fr
Inventor
David A. Helmick
David Leslie Burin
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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 EP2149623A2 publication Critical patent/EP2149623A2/fr
Publication of EP2149623A3 publication Critical patent/EP2149623A3/fr
Withdrawn legal-status Critical Current

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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
    • 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
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/325—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with layers graded in composition or in physical properties
    • 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
    • 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
    • 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
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • 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
    • F05C2201/0463—Cobalt
    • 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
    • F05D2300/11—Iron
    • 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
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/134—Zirconium
    • 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
    • Y10T428/12542—More than one such component
    • Y10T428/12549—Adjacent to each other

Definitions

  • This invention generally relates to protective coatings for metal alloy components exposed to high temperature gas environments and severe operating conditions, such as the working components of gas turbine engines used in electrical power generation. More particularly, the invention relates to a thermal barrier coating (TBC) for use in gas turbine engines and a method for producing a TBC coating.
  • TBC thermal barrier coating
  • Erosion generally refers to the process whereby a surface, particularly metal, is bombarded by contaminant particles of sufficiently high energy that cause other particles to be ejected (eroded) from the surface, resulting in degradation and cracking of the substrate material.
  • Ceramic coatings have been used in conjunction with a bond coating formed from an oxidation-resistant alloy such as MCrAlY, where M is iron, cobalt, and/or nickel, or from a diffusion aluminide or platinum aluminide that forms an oxidation-resistant intermetallic.
  • MCrAlY oxidation-resistant alloy
  • these bond coatings form an oxide layer or "scale” that chemically bonds to the ceramic layer to form the final bond coating.
  • ZrO 2 zirconia
  • MgO magnesia
  • YSZ Yttria-stabilized zirconia
  • the YSZ is deposited on the metal substrate using known methods, such as air plasma spraying (APS), low pressure plasma spraying (LPPS), as well as by physical vapor deposition (PVD) techniques such as electron beam physical vapor deposition (EBPVD).
  • APS air plasma spraying
  • LPPS low pressure plasma spraying
  • PVD physical vapor deposition
  • EBPVD electron beam physical vapor deposition
  • YSZ deposited by EBPVD is characterized by a strain-tolerant columnar grain structure that enables the substrate to expand and contract without causing damaging stresses that lead to spallation.
  • the strain-tolerant nature of such systems may be known. See generally U.S. Patent No. 6,730,413 for a description of a known thermal barrier coating system.
  • the present invention may generally relate to a process involving inducing cracks or microcracks in a post-coating application. This may facilitate the thermal barrier coating be applied densely, which may be easier to accomplish. After application, the coating may be selectively cracked, e.g., using shockwave exposure.
  • Laser peening is well known and understood in the art. For example, laser peening has been used to create a compressively stressed protection layer at the outer surface of a workpiece which is known to considerably increase the resistance of the workpiece to fatigue failure as disclosed in U.S. Patent No. 4,937,421 . Laser shock peening has also been used create deep compressive residual stresses into a turbine blade as disclosed in U.S. Patent No. 5,591,009 .
  • an embodiment may generally relate to a method for forming cracks in a thermal barrier coating applied to a gas turbine component.
  • the method may include the following steps: depositing a bond coating on a metallic substrate, wherein the bond coating comprises MCrAlY, where M is iron, cobalt, and/or nickel, and wherein the metallic substrate comprises a gas turbine component; depositing a thermal barrier coating on the bond coating, wherein the thermal barrier coating comprises yttria-stabilized zirconia; subjecting at least a portion of the thermal barrier coating to a shockwave such that microcracks are formed in the thermal barrier coating and such that the metallic substrate is not substantially deformed.
  • an embodiment may generally relate to a method of forming cracks in a ceramic-based coating.
  • the method may include the following steps: depositing a ceramic-based coating on a metallic-based substrate, wherein the ceramic-based coating comprises a thermal barrier coating; and subjecting at least a portion of the ceramic-based coating to a shockwave such that microcracks are formed in the ceramic-based coating and such that the metallic-based substrate is not substantially deformed.
  • thermal barrier coatings according to the present invention are applicable to various metal alloy components (so-called “superalloys”) that must still be protected from a thermally and chemically hostile environment.
  • superalloys include nozzles, buckets, shrouds, airfoils, and other hardware found in almost any gas turbine engine.
  • the coating may be any known TBC composition, e.g., it may consist of a thermal insulating ceramic layer whose composition and deposition significantly enhance the erosion resistance of the turbine components while maintaining a spallation resistance equivalent to or better than conventional coatings.
  • the coating composition may be applied then cracked after application.
  • High pressure turbine blades are prime examples of the substrates to which coatings in accordance with the invention can be applied.
  • turbine blades have an airfoil and a platform against which hot combustion gases are directed during operation of the gas turbine.
  • the airfoil surfaces are subjected to attack by oxidation, corrosion, and erosion.
  • the airfoil normally is anchored to a turbine disk with a dovetail formed on a root section of the blade.
  • FIGURE 1 shows a thermal barrier coating in accordance with the invention as applied to a substrate.
  • the coating 10 includes a thermal-insulating ceramic layer 12 over a bond coating 14 that overlies a metal alloy substrate 16 which may form the base material of the turbine blade. Suitable materials for the substrate include iron-, nickel-, and/or cobalt-based superalloys.
  • the bond coating may be oxidation resistant and may form an alumina layer 18 on the surface of the bond coating when the coated blade is exposed to elevated temperatures.
  • the alumina layer may protect the underlying superalloy substrate 16 from oxidation and may provide a surface to which the ceramic layer adheres.
  • cracks that have been formed so as to increase and/or induce strain tolerance.
  • Crack induction via shockwave exposure may enable the cracks to be placed in the material in particularly desirable areas and at specifically desirable densities.
  • coupled ablation may be used to induce a shockwave into a material.
  • the coupled ablation may be achieved through the use of a pulsed laser in a process similar to laser shock peening, where a laser is pulsed thorough the coupling material and into the ablative material thus creating a shockwave.
  • laser shock peening may be used to densify the material.
  • the resultant shockwave can induce microcracks within the coating to provide strain tolerance.
  • Other means of shockwave exposure may be possible.
  • Other means of coupled ablation may also be possible.
  • a strain tolerant TBC may be formed using laser shock peening.
  • a thermal barrier coating may be applied to a metallic substrate using an air plasma spray.
  • a bond coat may be MCrAlY (where M is iron, cobalt, and/or nickel), and the TBC may be 8% yttria-stabilized zirconia or any other ceramic-based coating used as a thermal barrier on turbine components.
  • the TBC may be laser shock peened.
  • the energy used to induce the microcracks in the TBC should preferably not substantially deform the substrate.
  • the energy should be relatively low because the coating may be very thin.
  • the energy of the shock wave would need be to sufficient to impart stress at or above the plastic yield of the substrate but below its compressive strength.
  • the energy used to induce microcracks in the TBC should be sufficient to impart stress above compressive strength of the TBC. Because the metallic substrate may be ductile, and the ceramic TBC may be brittle, there may be a particular level of energy that can be selected or determined.
  • Figure 2 schematically illustrates a general description of the amount of energy required to induce cracks in a TBC.
  • the amount of energy (per unit area) to fracture a material is represented by the area under the stress/strain curve.
  • Figure 2 illustrates a typical porous TBC coating.
  • the porosity reduces the "effective" cross-sectional area and therefore reducing the force required for fracture (because energy is a function of force not pressure or stress). This may effectively reduce the area under the curve considerably.
  • a thermal barrier coating experiences a shockwave (e.g., via laser ablation) and is fractured.
  • the energy that may be required may depend on the source of the shockwave, e.g., laser ablation or other, and/or the properties of material being cracked.
  • a process may produce a microstructural features (e.g., vertical cracks).
  • a microstructural features e.g., vertical cracks.
  • This may increase the durability of a turbine component and/or reduce manufacturing costs.
  • a simple dense coating may be applied to a component, and the vertical cracks can be induced in areas that they are needed. That is, cracks need not be introduced throughout an entire coating via processing parameters.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Inorganic Chemistry (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Ceramic Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP09161428A 2008-07-29 2009-05-28 Revêtements de barrière thermique et leurs procédés de production Withdrawn EP2149623A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/181,422 US20100028711A1 (en) 2008-07-29 2008-07-29 Thermal barrier coatings and methods of producing same

Publications (2)

Publication Number Publication Date
EP2149623A2 true EP2149623A2 (fr) 2010-02-03
EP2149623A3 EP2149623A3 (fr) 2010-12-15

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EP09161428A Withdrawn EP2149623A3 (fr) 2008-07-29 2009-05-28 Revêtements de barrière thermique et leurs procédés de production

Country Status (3)

Country Link
US (1) US20100028711A1 (fr)
EP (1) EP2149623A3 (fr)
JP (1) JP2010043351A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3239467A1 (fr) * 2016-04-27 2017-11-01 Siemens Aktiengesellschaft Aube mobile et turbomachine et carter
EP3071722B1 (fr) 2013-11-19 2018-08-29 Safran Aircraft Engines Procédé intégré de frittage pour microfissuration et tenue à l'érosion des barrières thermiques

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100136296A1 (en) * 2006-11-30 2010-06-03 United Technologies Corporation Densification of coating using laser peening
JP5769447B2 (ja) * 2011-02-28 2015-08-26 三菱重工業株式会社 遮熱コーティングの部分補修方法
US8906181B2 (en) 2011-06-30 2014-12-09 United Technologies Corporation Fan blade finishing
US9598973B2 (en) * 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same
EP2971686B1 (fr) * 2013-03-15 2018-10-17 United Technologies Corporation Articles revêtus et leurs procédés de fabrication
US20150125681A1 (en) 2013-11-06 2015-05-07 United Technologies Corporation High Temperature Imaging Media for Digital Image Correlation
JP5909274B2 (ja) * 2014-12-15 2016-04-26 三菱重工業株式会社 遮熱コーティングの部分補修方法
FR3055351B1 (fr) * 2016-08-25 2019-11-08 Safran Procede de realisation d'un systeme barriere thermique sur un substrat metallique d'une piece de turbomachine
US10174412B2 (en) * 2016-12-02 2019-01-08 General Electric Company Methods for forming vertically cracked thermal barrier coatings and articles including vertically cracked thermal barrier coatings
US10662891B2 (en) * 2017-04-04 2020-05-26 GM Global Technology Operations LLC Laser remelting to enhance cylinder bore mechanical properties
US10837298B2 (en) * 2018-08-21 2020-11-17 Chromalloy Gas Turbine Llc First stage turbine nozzle
EP3663706B1 (fr) 2018-12-06 2022-08-24 General Electric Company Procédé d'évaluation quantitative non invasive multicouche
CN113930710B (zh) * 2021-10-14 2023-09-26 广东省科学院新材料研究所 一种热障涂层材料、其制备方法及应用

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4937421A (en) 1989-07-03 1990-06-26 General Electric Company Laser peening system and method
US5591009A (en) 1995-01-17 1997-01-07 General Electric Company Laser shock peened gas turbine engine fan blade edges
US6544346B1 (en) * 1997-07-01 2003-04-08 General Electric Company Method for repairing a thermal barrier coating
US6730413B2 (en) 2001-07-31 2004-05-04 General Electric Company Thermal barrier coating
JP2004149915A (ja) * 2002-09-06 2004-05-27 Kansai Electric Power Co Inc:The 熱遮蔽セラミックコーティング部品とその製造方法

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4457948A (en) * 1982-07-26 1984-07-03 United Technologies Corporation Quench-cracked ceramic thermal barrier coatings
JPS62274062A (ja) * 1986-05-23 1987-11-28 Toyota Motor Corp セラミツク被覆部材の製造方法
US5352540A (en) * 1992-08-26 1994-10-04 Alliedsignal Inc. Strain-tolerant ceramic coated seal
JPH09327779A (ja) * 1996-06-07 1997-12-22 Mitsubishi Heavy Ind Ltd セラミック皮膜の割れ形成方法及び同方法によるセラミック皮膜部品
US6224963B1 (en) * 1997-05-14 2001-05-01 Alliedsignal Inc. Laser segmented thick thermal barrier coatings for turbine shrouds
US6120624A (en) * 1998-06-30 2000-09-19 Howmet Research Corporation Nickel base superalloy preweld heat treatment
WO2002103074A1 (fr) * 2001-06-15 2002-12-27 Mitsubishi Heavy Industries, Ltd. Materiau de revetement barriere thermique et son procede de production, element turbine a gaz utilisant ce materiau de revetement barriere thermique, et turbine a gaz
US6703137B2 (en) * 2001-08-02 2004-03-09 Siemens Westinghouse Power Corporation Segmented thermal barrier coating and method of manufacturing the same
US20070160859A1 (en) * 2006-01-06 2007-07-12 General Electric Company Layered thermal barrier coatings containing lanthanide series oxides for improved resistance to CMAS degradation
US7842402B2 (en) * 2006-03-31 2010-11-30 General Electric Company Machine components and methods of fabricating
JP5074123B2 (ja) * 2007-08-08 2012-11-14 株式会社日立製作所 高温耐摩耗性部材及び高温用耐摩耗部材の製造方法
US20100224602A1 (en) * 2009-03-06 2010-09-09 General Electric Company Method and system for removing thermal barrier coating

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4937421A (en) 1989-07-03 1990-06-26 General Electric Company Laser peening system and method
US5591009A (en) 1995-01-17 1997-01-07 General Electric Company Laser shock peened gas turbine engine fan blade edges
US6544346B1 (en) * 1997-07-01 2003-04-08 General Electric Company Method for repairing a thermal barrier coating
US6730413B2 (en) 2001-07-31 2004-05-04 General Electric Company Thermal barrier coating
JP2004149915A (ja) * 2002-09-06 2004-05-27 Kansai Electric Power Co Inc:The 熱遮蔽セラミックコーティング部品とその製造方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
KHOR K A ET AL: "SURFACE MODIFICATION OF PLASMA SPRAYED THERMAL BARRIER COATINGS BY PULSED LASER", SURFACE MODIFICATION TECHNOLOGIES, XX, XX, 1 January 1995 (1995-01-01), pages 793 - 799, XP008045036 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3071722B1 (fr) 2013-11-19 2018-08-29 Safran Aircraft Engines Procédé intégré de frittage pour microfissuration et tenue à l'érosion des barrières thermiques
EP3239467A1 (fr) * 2016-04-27 2017-11-01 Siemens Aktiengesellschaft Aube mobile et turbomachine et carter

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