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    HEAT INSULATING COATING SYSTEM FOR MEMBER MADE OF SUPERALLOY, MEMBER MADE OF SUPERALLOY AND METHOD FOR REDUCING WEIGHT OF MEMBER COATED WITH CERAMIC
    2.
    发明专利
    HEAT INSULATING COATING SYSTEM FOR MEMBER MADE OF SUPERALLOY, MEMBER MADE OF SUPERALLOY AND METHOD FOR REDUCING WEIGHT OF MEMBER COATED WITH CERAMIC 失效

    公开(公告)号：JP2000096261A

    公开(公告)日：2000-04-04

    申请号：JP16034699

    申请日：1999-06-08

    Applicant: UNITED TECHNOLOGIES CORP

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

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

    Abstract: PROBLEM TO BE SOLVED: To provide a heat insulating coating system having the advantage or reducing the weight and moreover limiting the oxidation even in the case ceramic is peeled. SOLUTION: In a heat insulating coating system 20 for a base material 22 made of a superalloy, a superalloy of a type capable of forming an adhesive alumina layer 26 is used. At first, a bonding coat 24 is applied to the local region of the base material 22 in such a manner that a part of the base material 22 is left exposed. The local region is ordinarily defined as the region in which heat insulating coating is first chipped such as the front edge and rear edge of airfoil or the like. Next, the alumina layer 26 is formed on the exposed part of the base material 22 and the bonding coat 24 by heat treatment. Successively, the alumina layer 26 is applied with a ceramic layer 28. In this way, even in the case the ceramic material 28 is peeled, the local bonding coat 24 is left, so that the oxidation of the base material can be limited.

    SEAL MECHANISM OF GAS TURBINE ENGINE
    3.
    发明专利
    SEAL MECHANISM OF GAS TURBINE ENGINE 失效

    公开(公告)号：JPH11229810A

    公开(公告)日：1999-08-24

    申请号：JP33516798

    申请日：1998-11-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

    IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16

    Abstract: PROBLEM TO BE SOLVED: To achieve an abrasive end portion for a seal mechanism of a gas turbine engine that receives a high degree of wear which is more durable, and the production of which is less expensive. SOLUTION: An abrasive end portion 28 includes a zirconium oxide wear coating 44 which is harder than a abraded seal surface such that it is able to grind the abraded seal surface, and which directly covers the top which has substantially no macrogrit. The coating 44 has a pillar-like structure and contains a stabilizer of approximately 3 wt.% to approximately 25 wt.%. The stabilizer may be selected from yttrium oxide, magnesium oxide, calcium oxide, or a mixture of these materials.

    5.
    发明专利
    未知

    公开(公告)号：DE60112382T2

    公开(公告)日：2006-06-01

    申请号：DE60112382

    申请日：2001-10-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZELESKY MARK F ,  GUPTA DINESH K ,  CETEL ALAN D

    IPC: C22C19/05 ,  C23C8/12 ,  C23C14/08 ,  C23C28/00 ,  C23C28/04 ,  F01D5/28

    Abstract: A low density superalloy and no bond coat thermal barrier coating system is described. The combination of alloy and TBC system can be used to fabricate light weight turbine blades with reduced blade pull. The present invention concerns nickel base superalloy articles which include additions of yttrium and hafnium that causes them to develop a durable, adherent aluminium oxide coating which will adhere to both the substrate and a ceramic thermal barrier coating thereby eliminating the need for an intermediate bond coat.

    6.
    发明专利
    未知

    公开(公告)号：DE69826096T2

    公开(公告)日：2005-09-29

    申请号：DE69826096

    申请日：1998-11-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

    IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16 ,  F01D5/28

    Abstract: A gas turbine engine seal system includes a rotating member 12;30 having an abrasive tip 28 disposed in use in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat 44 having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface. The coat 44 comprises zirconium oxide and about 3% to 25% of a stabilizer selected from yttrium oxide, magnesium oxide, calcium oxide or mixtures thereof.

    7.
    发明专利
    未知

    公开(公告)号：DE60112382D1

    公开(公告)日：2005-09-08

    申请号：DE60112382

    申请日：2001-10-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZELESKY MARK F ,  GUPTA DINESH K ,  CETEL ALAN D

    IPC: C22C19/05 ,  C23C8/12 ,  C23C28/00 ,  C23C28/04 ,  F01D5/28 ,  C23C14/08

    Abstract: A low density superalloy and no bond coat thermal barrier coating system is described. The combination of alloy and TBC system can be used to fabricate light weight turbine blades with reduced blade pull. The present invention concerns nickel base superalloy articles which include additions of yttrium and hafnium that causes them to develop a durable, adherent aluminium oxide coating which will adhere to both the substrate and a ceramic thermal barrier coating thereby eliminating the need for an intermediate bond coat.

    8.
    发明专利
    未知

    公开(公告)号：DE69903595D1

    公开(公告)日：2002-11-28

    申请号：DE69903595

    申请日：1999-06-11

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F01D5/28 ,  C23C4/00 ,  C23C4/08 ,  C23C28/00 ,  F01D5/18 ,  F02C7/00 ,  C23C4/02

    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.

    9.
    发明专利
    未知

    公开(公告)号：FR2716237A1

    公开(公告)日：1995-08-18

    申请号：FR9501793

    申请日：1995-02-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MELVIN FRELING ,  GUPTA DINESH K

    IPC: F02C7/00 ,  B64C1/40 ,  C23C4/02 ,  F01D21/04 ,  F02C7/24 ,  F02C7/25

    Abstract: In a gas turbine engine, a method and apparatus for containing molten materials and ignited titanium and titanium alloys within the confines of the turbine engine environment. The method includes the step of first applying a bond coating to the inner surface of the outer compressor casing. The bond coating is then plasma oversprayed with a non-reactive, thermally insulative ceramic top coating. The apparatus includes a substrate having a bond coating and a ceramic top coating, surrounding at least a portion of the gas turbine engine, for containing turbine engine fires within the turbine engine environment. Preferably, the bond coating is a Ni-Co-Cr-Al-Y alloy, and the top coat is stabilized zirconia.

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