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    Thermal barrier coating system utilizing lcalized bond coat and article having the same
    11.
    发明专利
    Thermal barrier coating system utilizing lcalized bond coat and article having the same 未知

    公开(公告)号：SG75960A1

    公开(公告)日：2000-10-24

    申请号：SG1999002587

    申请日：1999-05-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BOSE SUDHANGSHU ,  GUPTA DINESH K ,  MARCIN JEANINE T ,  ULION NICHOLAS E

    IPC: F01D5/28 ,  C23C4/00 ,  C23C4/08 ,  C23C28/00 ,  F01D5/18 ,  F02C7/00

    Abstract: A thermal barrier coating system for a superalloy substrate is disclosed. The superalloy is preferably of the type that is capable of forming an adherent alumina layer. A bond coat is applied to a local area of the substrate (24), so that a portion of the substrate remains exposed. The localized area is defined to be the area(s) at which a TBC typically fails first, e.g., the leading (30) and trailing edges (32) of an airfoil (20), or other area. An alumina layer (26) is formed on the remaining portion of the substrate, and also on the bond coat. A ceramic layer (28) is then applied on the alumina layer. Even if the ceramic material is removed, the localized bond coat remains, and reduces the rate at which the underlying substrate oxidizes. A coated article is also disclosed, as is a system that utilizes a conventional superalloy and aluminide coating with the localized bond coat.

    16.
    发明专利
    未知

    公开(公告)号：DE69914409D1

    公开(公告)日：2004-03-04

    申请号：DE69914409

    申请日：1999-06-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： RISTAU RAYMOND P ,  BOSE SUDHANGSHU ,  CETEL ALAN D

    IPC: C23C8/10 ,  C23C14/02 ,  C23G1/00 ,  C23C28/04

    Abstract: A method of preparing a superalloy component to receive a ceramic thermal barrier coating without an intermediate bond coat is disclosed. The superalloy substrate is degreased, abrasively cleaned, ultrasonically cleaned, washed in an aqueous bath containing a wetting agent, rinsed at least once, and then heat treated in an atmosphere that is non-reactive with the substrate and alumina at a temperature and time sufficient to form a surface alumina layer which is predominantly alumina.

    THERMAL BARRIER COATING SYSTEM UTILIZING LOCALIZED BOND COATAND ARTICLE HAVING THE SAME
    17.
    发明专利
    THERMAL BARRIER COATING SYSTEM UTILIZING LOCALIZED BOND COATAND ARTICLE HAVING THE SAME 未知

    公开(公告)号：CA2274412A1

    公开(公告)日：1999-12-12

    申请号：CA2274412

    申请日：1999-06-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BOSE SUDHANGSHU ,  MARCIN JEANINE T ,  GUPTA DINESH K ,  ULION NICHOLAS E

    IPC: F01D5/28 ,  C23C4/00 ,  C23C4/08 ,  C23C28/00 ,  F01D5/18 ,  F02C7/00 ,  C23C4/10

    Abstract: A thermal barrier coating system for a superalloy substrate is disclosed. The superalloy is preferably of the type that is capable of forming an adherent alumina layer. A bond coat is applied to a local area of the substrate, so that a portion of the substrate remains exposed. The localized area is defined to be the areas) at which a TBC typically fails first, e.g., the leading and trailing edges of an airfoil, or other area. An alumina layer is formed on the remaining portion of the substrate, and also on the bond coat. A ceramic layer is then applied on the alumina layer. Even if the ceramic material is removed, the localized bond coat remains, and reduces the rate at which the underlying substrate oxidizes. A coated article is also disclosed, as is a system that utilizes a conventional superalloy and aluminide coating with the localized bond coat.

    20.
    发明专利
    未知

    公开(公告)号：DE60331203D1

    公开(公告)日：2010-03-25

    申请号：DE60331203

    申请日：2003-03-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BOSE SUDHANGSHU ,  CETEL ALAN D ,  DRAGHI PETER J ,  PIETRUSKA NORMAN

    IPC: C23C4/02 ,  F01D5/14 ,  B23P6/00 ,  C23C10/02 ,  C23G1/20 ,  F01D5/00 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00

    Abstract: The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.

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