EP0605196A1 - Procédé pour la formation d'un revêtement faisant effet de barrière thermique - Google Patents

Procédé pour la formation d'un revêtement faisant effet de barrière thermique Download PDF

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Publication number
EP0605196A1
EP0605196A1 EP93310442A EP93310442A EP0605196A1 EP 0605196 A1 EP0605196 A1 EP 0605196A1 EP 93310442 A EP93310442 A EP 93310442A EP 93310442 A EP93310442 A EP 93310442A EP 0605196 A1 EP0605196 A1 EP 0605196A1
Authority
EP
European Patent Office
Prior art keywords
zirconia layer
substrate
bondcoat
zirconia
layer
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Withdrawn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
EP93310442A
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German (de)
English (en)
Inventor
Adrian Maurice Beltran
Robert Scott Shalvoy
Yuk-Chiu Lau
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP0605196A1 publication Critical patent/EP0605196A1/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Withdrawn legal-status Critical Current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
    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/129—Flame spraying
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying

Definitions

  • This invention relates to a process for providing a thermal barrier coating on industrial gas turbine components such as combustion liners and transition pieces.
  • Thermal barriercoating (TBC) systems are widely used in high temperature applications to provide oxidation and thermal resistance protection to metallic substrates under high thermal gradient conditions.
  • Conventional TBC's are applied by various powder spray deposition processes, and consist of an intermediate metallic bondcoat attached to the substrate and a topcoat of stabilized zirconia.
  • the zirconia may be phase-stabilized with between 6 and 22 weight percent yttria, or alternatively, magnesia, ceria or similar oxides. These coatings typically exhibit an un- cracked but porous microstructure. This type of processing is done with minimal substrate preheat, and is limited to a maximum coating thickness of 25 to 30 mil.
  • thermal cycling resistance is significantly reduced due to coating spallation via cracking and separation between the bondcoat and initial zirconia deposit at that interface.
  • Control of the initial zirconia layers deposited via this process is critical to the thermal cycling resistance of this TBC. In part, control is achieved through process parameter optimization and per-pass powder injection rates which are generally lowerthan conventional processing. Hence, this coating has a higher thermal conductivity per unit thickness than the porous conventional coating described above, by as much as 30 to 50%. Therefore, this coating may have an effective thermal resistance only one-third that of its absolute thickness advantage.
  • the objective of this invention is to provide a superior TBC coating through plasma spray deposition of an initial zirconia deposit with a columnar microstructure achieved with controlled substrate preheat.
  • This first or inner layer promotes good adherence, and is followed by a smooth, in-process transition to conditions which favor deposition of a controlled porosity, highly thermal resistive zirconia outer layer.
  • a more specific objective of this invention is to provide a cost-effective coating process for large surface area components such as industrial landbased gas turbine combustion liners and transition pieces, which typically require TBC coatings over 1500-2000 square inches of surface area.
  • this two-layer zirconia TBC microstructure is that it maximizes thermal cycling resistance and thermal resistivity at an overall lower coating thickness. This will result in reduced manufacturing cycle time and cost. Further reductions in cycle time may be achieved through increases in powder deposition rates, particularly for the outer zirconia layer, since a porous structure may be easier to achieve and control in this manner.
  • the coating process of this invention thus produces a thermally resistant surface layer comprised of two layers (transitioned through grading of porosity) of stabilized zirconia ceramic attached to an oxidation and corrosion resistant metallic bondcoat, which is itself metallurgically bonded to a metallic substrate.
  • an air plasma spray process used to deposit the inner stabilized-zirconia layer is controlled to produce a dense, columnar microstructure which has lower thermal resistivity, but which is extremely well adhered to the metallic bondcoat and which also provides maximum thermal cycling resistance to the composite, multi-layered coating system.
  • the outer stabilized zirconia layer is applied by the air plasma spray deposition process to produce a controlled microstructure containing minimal cracks and approximately 10 to 20% porosity, which enhances thermal resistivity of the layer.
  • a process for applying a thermal barrier coating to a metallic substrate which comprises the steps of:
  • the invention relates to a gas turbine component having a thermal barrier coating thereon, applied by the above described process.
  • FIGURE 1 is a cross section of a metal substrate provided with a thermal barrier coating in accordance with a first exemplary embodiment of the invention.
  • a schematic illustration of an exemplary embodiment of the invention is shown to include a metallic substrate material 10 with a bondcoat 12 metallurgically bonded thereto.
  • the substrate 10 may be, for example, a large superalloy surface area component of an industrial gas turbine engine. More specifically, the substrate may be a combustion liner or a transition piece (connecting the combustion chamber to the turbine) or other large component which typically requires a thermal barrier coating over 1500-2000 square inches of surface area.
  • the metallic bondcoat 12 may be applied by a variety of thermal spray processes including air or vacuum plasma, or High Velocity Oxy-Fuel (HVOF) deposition to a suitable thickness, and may comprise MCrAIY chemical compositions, where M is Co, Ni, Fe or combinations of these elements.
  • one such bondcoat may comprise 10-30% weight Chromium, 3-13 wt.% aluminum, and 0.05 to 1.0wt.% yttrium or other rare earth elements, and the balance M.
  • An inner stabilized zirconia deposit layer 14 is applied to the bondcoat 12 by an air plasma spray process.
  • the process is controlled (by substrate preheat) to produce a dense (i.e., substantially zero porosity), columnar microstructure which has lower thermal resistivity, but which is extremely well adhered to the metallic bondcoat 12.
  • graded layers transitioning from all metal to all non-metallic
  • the substrate temperature is initially elevated to a temperature in excess of 600°F. and up to about 1200°F. or higher to provide the dense, columnar microstructure.
  • the thickness of this inner layer 14 is preferably between about 2 and about 20 mil, but may be greater. This inner layer 14 provides maximum thermal cycling resistance to the composite, multi-layered coating system.
  • the process is continued under conditions which favor the deposition of a controlled porosity, highly thermal resistive zirconia outer layer 16, having a thickness of between about 10 and about 45 mi
  • the outer zirconia layer 16 is also applied by the air plasma spray deposition process to produce a controlled microstructure containing minimal cracks and approximately a 10 to 20% porosity, which enhances the thermal resistivity of the layer. This is achieved by permitting the substrate 10 to cool to a lower temperature, between ambient and up to about 600°F. As a result of the continuity of the process, a transition zone between the inner and outer layers is created which has a porosity of between 0 and about 10%.
  • This two-layer zirconia TBC microstructure is that it maximizes thermal cycling resistance and thermal resistivity at a lower total coating thickness. This will result in reduced manufacturing cycle time and cost. Further reductions in cycle time may be achieved through increases in powder deposition rates, particularly for the outer zirconia layer, since a porous structure may be easier to achieve and control in this manner.
EP93310442A 1992-12-29 1993-12-22 Procédé pour la formation d'un revêtement faisant effet de barrière thermique Withdrawn EP0605196A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US99692092A 1992-12-29 1992-12-29
US996920 1992-12-29

Publications (1)

Publication Number Publication Date
EP0605196A1 true EP0605196A1 (fr) 1994-07-06

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP93310442A Withdrawn EP0605196A1 (fr) 1992-12-29 1993-12-22 Procédé pour la formation d'un revêtement faisant effet de barrière thermique

Country Status (5)

Country Link
EP (1) EP0605196A1 (fr)
JP (1) JPH06235074A (fr)
KR (1) KR940014878A (fr)
CA (1) CA2110007A1 (fr)
NO (1) NO934862L (fr)

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0705911A1 (fr) * 1994-10-04 1996-04-10 General Electric Company Revêtement de barrière thermique
GB2296503A (en) * 1994-12-28 1996-07-03 Gen Electric Thrmal barrier coating having grooves for enhanced strain tolerance
WO1996035826A1 (fr) * 1995-05-08 1996-11-14 Alliedsignal Inc. Revetement poreux formant une barriere thermique
EP0765951A2 (fr) * 1995-09-26 1997-04-02 United Technologies Corporation Revêtement céramique résistant
GB2317400A (en) * 1996-09-19 1998-03-25 Toshiba Kk Thermal barrier coating providing reaction sintering suppression
EP0916635A2 (fr) * 1997-11-18 1999-05-19 United Technologies Corporation Revêtements céramiques à porosité stratifiée
WO1999035306A2 (fr) * 1997-12-09 1999-07-15 N.V. Interturbine Structure de ceramique pour couche d'isolation thermique
WO2000009778A1 (fr) * 1998-08-11 2000-02-24 Siemens Westinghouse Power Corporation Systeme de revetement a barriere thermique multicouches
US6287644B1 (en) 1999-07-02 2001-09-11 General Electric Company Continuously-graded bond coat and method of manufacture
EP1295964A3 (fr) * 2001-09-24 2004-01-14 Siemens Westinghouse Power Corporation Revêtement barrière thermique à double microstructure
WO2004029330A1 (fr) * 2002-09-25 2004-04-08 Volvo Aero Corporation Revetement barriere thermique et son procede d'application
EP1731630A2 (fr) * 2005-06-10 2006-12-13 The General Electric Company Barrière thérmique et procédé pour sa fabrication
EP1780308A2 (fr) * 2005-10-27 2007-05-02 The General Electric Company Méthode et appareil pour la fabrication d'un composant
US7258934B2 (en) 2002-09-25 2007-08-21 Volvo Aero Corporation Thermal barrier coating and a method of applying such a coating
WO2007112783A1 (fr) * 2006-04-06 2007-10-11 Siemens Aktiengesellschaft Revetement stratifie formant une barriere thermique a porosite elevee et composant
EP1852524A2 (fr) * 2006-05-01 2007-11-07 The General Electric Company Procédé de fabrication de barrières thermiques ayant un isolation thermique améliorée
EP1889940A2 (fr) 2006-08-18 2008-02-20 United Technologies Corporation Revêtement de barrière thermique doté d'une couche supérieure à pulvérisation plasma
WO2009097834A1 (fr) 2008-02-06 2009-08-13 Forschungszentrum Jülich GmbH Système de couches calorifuges et son procédé de fabrication
EP2196559A1 (fr) 2008-12-15 2010-06-16 ALSTOM Technology Ltd Système de revêtement de barrière thermique, composants revêtus avec celle-ci et procédé pour l'application d'un système de revêtement de barrière thermique à des composants
EP2108715A3 (fr) * 2008-04-08 2010-12-08 General Electric Company Système de revêtement de barrière thermique et procédés de revêtement pour plateau de moteur de turbine à gaz
EP2281924A1 (fr) * 2009-08-04 2011-02-09 United Technologies Corporation Revêtements de barrière thermique structurellement différents
RU2445199C2 (ru) * 2010-03-25 2012-03-20 Общество с ограниченной ответственностью "Производственное предприятие Турбинаспецсервис" Способ упрочнения блока сопловых лопаток турбомашин из никелевых и кобальтовых сплавов
WO2013107712A1 (fr) * 2012-01-16 2013-07-25 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Procédé de réalisation d'une couche céramique sur une surface formée à partir d'un alliage à base de nickel
CN101698364B (zh) * 2009-11-03 2013-08-28 西安交通大学 一种热障涂层及其制备工艺
JP2014224325A (ja) * 2014-08-26 2014-12-04 三菱重工業株式会社 機械部品のコーティング方法及び機械部品
US9023486B2 (en) 2011-10-13 2015-05-05 General Electric Company Thermal barrier coating systems and processes therefor
US9034479B2 (en) 2011-10-13 2015-05-19 General Electric Company Thermal barrier coating systems and processes therefor
DE102014222686A1 (de) * 2014-11-06 2016-05-12 Siemens Aktiengesellschaft Doppellagige Wärmedämmschicht durch unterschiedliche Beschichtungsverfahren
US10280765B2 (en) 2013-11-11 2019-05-07 United Technologies Corporation Article with coated substrate
RU2697758C1 (ru) * 2019-01-14 2019-08-19 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" Способ нанесения жаростойких покрытий y-мо-о из плазмы вакуумно-дугового разряда
RU2702515C1 (ru) * 2018-06-06 2019-10-08 Общество с ограниченной ответственностью "Научно-производственное предприятие "Уралавиаспецтехнология" Способ упрочняющей обработки детали из сплава на никелевой основе (варианты)
CN113088859A (zh) * 2021-03-30 2021-07-09 潍柴动力股份有限公司 复合涂层、活塞、发动机和车辆

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SE527179C2 (sv) * 2003-12-05 2006-01-17 Sandvik Intellectual Property Tunnfilmssolcell eller tunnfilmsbatteri, innefattande en zirkoniumoxidbelagd bandprodukt av ferritiskt kromstål
JP4645030B2 (ja) * 2003-12-18 2011-03-09 株式会社日立製作所 遮熱被膜を有する耐熱部材
US7354663B2 (en) 2004-04-02 2008-04-08 Mitsubishi Heavy Industries, Ltd. Thermal barrier coating, manufacturing method thereof, turbine part and gas turbine

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EP0366924A2 (fr) * 1988-11-03 1990-05-09 AlliedSignal Inc. Rêvetement céramique en tant que barrière thermique comportant une couche intermédiaire en alumine
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EP0183638A1 (fr) * 1984-11-28 1986-06-04 United Technologies Corporation Procédé pour appliquer une couche métallocéramique à gradation continue à des substrats métalliques
EP0185603A1 (fr) * 1984-11-28 1986-06-25 United Technologies Corporation Amélioration de la résistance à l'usure d'un joint d'étanchéité d'une turbine constitué d'un matériau métal céramique
US4613259A (en) * 1984-11-28 1986-09-23 United Technologies Corporation Apparatus for controlling powder flow rate in a carrier gas
EP0366924A2 (fr) * 1988-11-03 1990-05-09 AlliedSignal Inc. Rêvetement céramique en tant que barrière thermique comportant une couche intermédiaire en alumine
WO1992005298A1 (fr) * 1990-09-20 1992-04-02 United Technologies Corporation Enduit en ceramique a structure colonnaire destine a servir de barriere thermique et avec adherence amelioree
WO1993018199A1 (fr) * 1992-03-05 1993-09-16 Rolls-Royce Plc Article revetu

Cited By (56)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0705911A1 (fr) * 1994-10-04 1996-04-10 General Electric Company Revêtement de barrière thermique
US5830586A (en) * 1994-10-04 1998-11-03 General Electric Company Thermal barrier coatings having an improved columnar microstructure
GB2296503B (en) * 1994-12-28 1998-10-21 Gen Electric Thick thermal barrier coating having grooves for enhanced strain tolerance
GB2296503A (en) * 1994-12-28 1996-07-03 Gen Electric Thrmal barrier coating having grooves for enhanced strain tolerance
US5681616A (en) * 1994-12-28 1997-10-28 General Electric Company Thick thermal barrier coating having grooves for enhanced strain tolerance
WO1996035826A1 (fr) * 1995-05-08 1996-11-14 Alliedsignal Inc. Revetement poreux formant une barriere thermique
US5624721A (en) * 1995-05-08 1997-04-29 Alliedsignal Inc. Method of producing a superalloy article
US6102656A (en) * 1995-09-26 2000-08-15 United Technologies Corporation Segmented abradable ceramic coating
EP0765951A2 (fr) * 1995-09-26 1997-04-02 United Technologies Corporation Revêtement céramique résistant
US5780171A (en) * 1995-09-26 1998-07-14 United Technologies Corporation Gas turbine engine component
US5705231A (en) * 1995-09-26 1998-01-06 United Technologies Corporation Method of producing a segmented abradable ceramic coating system
EP0765951A3 (fr) * 1995-09-26 1997-05-14 United Technologies Corp
GB2317400B (en) * 1996-09-19 1999-02-24 Toshiba Kk Thermal barrier coating memner and method of producing the same
GB2317400A (en) * 1996-09-19 1998-03-25 Toshiba Kk Thermal barrier coating providing reaction sintering suppression
US5906895A (en) * 1996-09-19 1999-05-25 Kabushiki Kaisha Toshiba Thermal barrier coating member and method of producing the same
EP0916635A3 (fr) * 1997-11-18 2001-02-28 United Technologies Corporation Revêtements céramiques à porosité stratifiée
EP0916635A2 (fr) * 1997-11-18 1999-05-19 United Technologies Corporation Revêtements céramiques à porosité stratifiée
KR100631447B1 (ko) * 1997-11-18 2006-12-04 유나이티드 테크놀로지스 코포레이션 다공성을갖는적층된세라믹코팅
WO1999035306A3 (fr) * 1997-12-09 1999-10-07 Interturbine Nv Structure de ceramique pour couche d'isolation thermique
WO1999035306A2 (fr) * 1997-12-09 1999-07-15 N.V. Interturbine Structure de ceramique pour couche d'isolation thermique
WO2000009778A1 (fr) * 1998-08-11 2000-02-24 Siemens Westinghouse Power Corporation Systeme de revetement a barriere thermique multicouches
US6106959A (en) * 1998-08-11 2000-08-22 Siemens Westinghouse Power Corporation Multilayer thermal barrier coating systems
US6287644B1 (en) 1999-07-02 2001-09-11 General Electric Company Continuously-graded bond coat and method of manufacture
EP1295964A3 (fr) * 2001-09-24 2004-01-14 Siemens Westinghouse Power Corporation Revêtement barrière thermique à double microstructure
WO2004029330A1 (fr) * 2002-09-25 2004-04-08 Volvo Aero Corporation Revetement barriere thermique et son procede d'application
US7258934B2 (en) 2002-09-25 2007-08-21 Volvo Aero Corporation Thermal barrier coating and a method of applying such a coating
EP1731630A3 (fr) * 2005-06-10 2007-08-01 General Electric Company Barrière thérmique et procédé pour sa fabrication
EP1731630A2 (fr) * 2005-06-10 2006-12-13 The General Electric Company Barrière thérmique et procédé pour sa fabrication
US7910173B2 (en) 2005-06-10 2011-03-22 General Electric Company Thermal barrier coating and process therefor
US7597966B2 (en) 2005-06-10 2009-10-06 General Electric Company Thermal barrier coating and process therefor
EP1780308A3 (fr) * 2005-10-27 2007-09-26 General Electric Company Méthode et appareil pour la fabrication d'un composant
EP1780308A2 (fr) * 2005-10-27 2007-05-02 The General Electric Company Méthode et appareil pour la fabrication d'un composant
WO2007112783A1 (fr) * 2006-04-06 2007-10-11 Siemens Aktiengesellschaft Revetement stratifie formant une barriere thermique a porosite elevee et composant
EP1852524A2 (fr) * 2006-05-01 2007-11-07 The General Electric Company Procédé de fabrication de barrières thermiques ayant un isolation thermique améliorée
EP1852524A3 (fr) * 2006-05-01 2008-05-21 The General Electric Company Procédé de fabrication de barrières thermiques ayant un isolation thermique améliorée
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CA2110007A1 (fr) 1994-06-30
JPH06235074A (ja) 1994-08-23
KR940014878A (ko) 1994-07-19
NO934862D0 (no) 1993-12-28
NO934862L (no) 1994-06-30

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