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    METHOD FOR REPAIRING VANE
    1.
    发明专利
    METHOD FOR REPAIRING VANE 审中-公开

    公开(公告)号：JP2003161111A

    公开(公告)日：2003-06-06

    申请号：JP2002309850

    申请日：2002-10-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HISKES DAVID J

    IPC: F01D9/02 ,  B23P6/00 ,  F01D5/00 ,  F01D25/00 ,  F02C7/00

    Abstract: PROBLEM TO BE SOLVED: To provide a method of repairing a vane which leaves no welded portion on an airfoil. SOLUTION: A method of repairing which comprises the steps of: preparing a vane (10) having an inside platform (11), an inside buttress (12), an outside platform (13), an outside buttress (14), and an airfoil (16); completely removing the inside platform (11), the inside buttress (12), the airfoil (16) from the vane (10), and removing one partial portion of the outside platform (13) and the outside buttress (14) by leaving a machined vane portion as it is simultaneously; further, preparing replacement details having a replacement of the inside platform, a replacement of the inside buttress, and a replacement of the airfoil; and arranging the replacement details for the machined vane portion and bonding them together. COPYRIGHT: (C)2003,JPO

    Method for repairing a turbine vane
    3.
    发明专利
    Method for repairing a turbine vane 未知

    公开(公告)号：GB2381224A

    公开(公告)日：2003-04-30

    申请号：GB0221936

    申请日：2002-09-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HISKES DAVID J

    IPC: F01D9/02 ,  B23P6/00 ,  F01D5/00 ,  F01D25/00 ,  F02C7/00 ,  B23P15/00 ,  B23P15/04

    Abstract: A method for repairing a vane 10 used in a gas turbine engine comprises the steps of providing a vane 10 to be repaired, which vane 10 has a first platform 11, a first buttress 12, a second platform 13, a second buttress 14, and an airfoil 16 extending between the first and second platforms 11, 13, removing the first platform 11, the first buttress 12, and the airfoil 16 from the vane 10 in their entirety and removing part of the second platform 13 and the second buttress 14 leaving a machined vane portion 15, providing a replacement detail 40 having at least a replacement first platform 43, a replacement first buttress 44 and a replacement airfoil 42, positioning the replacement detail 40 relative to the machined vane portion 15, and forming a joint between the machined vane portion 15 and the replacement detail 40.

    METHOD FOR REPAIRING A TURBINE VANE
    4.
    发明专利
    METHOD FOR REPAIRING A TURBINE VANE 未知

    公开(公告)号：SG131751A1

    公开(公告)日：2007-05-28

    申请号：SG2002059145

    申请日：2002-09-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HISKES DAVID J

    IPC: F01D9/02 ,  B23P6/00 ,  F01D5/00 ,  F01D25/00 ,  F02C7/00

    Abstract: The present invention relates to method for repairing a vane used in a gas turbine engine. The method broadly comprises the steps of providing a vane to be repaired, which vane has a first platform, a first buttress, a second platform, a second buttress and an airfoil extending between the first and second platforms, removing the first platform, the first buttress, and the airfoil from the vane in their entirety and removing part of the second platform and the second buttress leaving a machined vane portion, providing a replacement first buttress and a replacement airfoil, positioning the replacement detail relative to the machined vane portion, and forming a joint between the machined vane portion ant the replacement detail.

    SPLIT VANE REPAIR
    7.
    发明专利
    SPLIT VANE REPAIR 未知

    公开(公告)号：SG148099A1

    公开(公告)日：2008-12-31

    申请号：SG2008032971

    申请日：2008-04-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PELLET PAUL M ,  HISKES DAVID J

    Abstract: SPLIT VANE REPAIR A method of repairing a vane cluster for a gas turbine engine includes attaching a first registration block to a salvageable airfoil segment of the vane cluster, machining a face of the first registration block relative to datum surfaces of the vane cluster, removing a damaged airfoil segment from the vane cluster, adding new material to the salvageable airfoil segment, joining a replacement airfoil segment having a second registration block to the salvageable airfoil segment to replace the damaged airfoil segment, removing the first registration block, and removing the second registration block. The respective first and second registration blocks of the salvageable airfoil segment and the replacement airfoil segment are aligned in a configuration substantially identical to a configuration of the vane cluster prior to undergoing repair.

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