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20 条记录 (耗时 0.031 秒)

    TRAILING EDGE MACHINING OF A WORKPIECE
    3.
    发明申请
    TRAILING EDGE MACHINING OF A WORKPIECE 有权
    工作的边缘加工

    公开(公告)号：US20100252533A1

    公开(公告)日：2010-10-07

    申请号：US12417714

    申请日：2009-04-03

    申请人： Carl W. Mercier ,  Daniel E. Quinn ,  David J. Hiskes ,  Paul M. Pellet ,  Michael L. Miller

    发明人： Carl W. Mercier ,  Daniel E. Quinn ,  David J. Hiskes ,  Paul M. Pellet ,  Michael L. Miller

    IPC分类号： B23H1/04 ,  B23H1/00

    CPC分类号： B23H9/10 ,  B23H11/003 ,  B23Q3/063 ,  B24B19/14 ,  B24B41/06

    摘要： A method of securing an workpiece for machining the trailing edge. The workpiece has a platform from which extends an airfoil, the airfoil including a leading edge and a trailing edge, and a pressure side and a suction side. A fixture with at least one locating datum that relates to the platform and at least one locating datum that relates to the leading edge is provided. The fixture does not contact the trailing edge of the workpiece. The workpiece is positioned so that the platform is against the related locating datum and the leading edge is against the related locating datum. The workpiece is secured within the fixture, and the trailing edge of the workpiece is machined.

    摘要翻译： 一种固定用于加工后缘的工件的方法。 工件具有一个平台，从该平台延伸翼型件，该翼型件包括前缘和后缘，以及压力侧和吸力侧。 提供具有至少一个与平台相关的定位基准的固定装置和至少一个与前缘相关的定位基准。 夹具不接触工件的后缘。 工件被定位成使得平台抵靠相关的定位基准，并且前缘抵靠相关的定位基准。 工件被固定在固定装置内，并且加工工件的后缘。

    Split vane repair
    6.
    发明申请
    Split vane repair 有权
    拆分叶片修复

    公开(公告)号：US20080289179A1

    公开(公告)日：2008-11-27

    申请号：US11805136

    申请日：2007-05-22

    申请人： Paul M. Pellet ,  David J. Hiskes

    发明人： Paul M. Pellet ,  David J. Hiskes

    IPC分类号： B23P6/00

    CPC分类号： F01D5/005 ,  B23P6/002 ,  F01D9/044 ,  F01D25/285 ,  F05D2230/64 ,  F05D2230/80 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49321 ,  Y10T29/49336 ,  Y10T29/49337

    摘要： 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.

    摘要翻译： 一种维修燃气涡轮发动机的叶片簇的方法包括将第一对准块附接到叶片组的可抢救的翼型段，相对于叶片簇的基准面加工第一对准块的面，去除损坏的翼型段 从叶片组中将新材料添加到可救修的翼型段，将具有第二对准块的替换翼型段连接到可补救的翼型段，以替换损坏的翼型段，移除第一登记块，并且移除第二登记块。 可补救的翼型段和替换翼型​​段的相应的第一和第二对准块在进行修理之前与叶片簇的构造基本相同的构型对准。

    Split vane cluster repair method
    7.
    发明授权
    Split vane cluster repair method 有权
    拆分叶片修复

    公开(公告)号：US08220150B2

    公开(公告)日：2012-07-17

    申请号：US11805136

    申请日：2007-05-22

    申请人： Paul M. Pellet ,  David J. Hiskes

    发明人： Paul M. Pellet ,  David J. Hiskes

    IPC分类号： B23P6/00

    CPC分类号： F01D5/005 ,  B23P6/002 ,  F01D9/044 ,  F01D25/285 ,  F05D2230/64 ,  F05D2230/80 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49321 ,  Y10T29/49336 ,  Y10T29/49337

    摘要： 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.

    摘要翻译： 一种维修燃气涡轮发动机的叶片簇的方法包括将第一对准块附接到叶片组的可抢救的翼型段，相对于叶片簇的基准面加工第一对准块的面，去除损坏的翼型段 从叶片组中将新材料添加到可救修的翼型段，将具有第二对准块的替换翼型段连接到可补救的翼型段，以替换损坏的翼型段，移除第一登记块，并且移除第二登记块。 可补救的翼型段和替换翼型​​段的相应的第一和第二对准块在进行修理之前与叶片簇的构造基本相同的构型对准。

    Oxidation-corrosion resistant coating
    10.
    发明授权
    Oxidation-corrosion resistant coating 有权
    耐氧化涂层

    公开(公告)号：US08354176B2

    公开(公告)日：2013-01-15

    申请号：US12470993

    申请日：2009-05-22

    申请人： Michael Minor ,  Paul M. Pellet ,  Michael L. Miller ,  Brian S. Tryon

    发明人： Michael Minor ,  Paul M. Pellet ,  Michael L. Miller ,  Brian S. Tryon

    IPC分类号： B32B15/00 ,  C22C19/05

    CPC分类号： C23C30/00 ,  C23C4/073 ,  C23C14/16 ,  Y10T428/12778 ,  Y10T428/12944

    摘要： A metallic coating for protecting a substrate from high temperature oxidation and hot corrosion environments comprising about 2.5 to about 13.5 wt. % cobalt, about 12 to about 27 wt. % chromium, about 5 to about 7 wt. % aluminum, about 0.0 to about 1.0 wt. % yttrium, about 0.0 to about 1.0 wt. % hafnium, about 1.0 to about 3.0 wt. % silicon, about 0.0 to about 4.5 wt. % tantalum, about 0.0 to about 6.5 wt. % tungsten, about 0.0 to about 2.0 wt. % rhenium, about 0.0 to about 1.0 wt. % molybdenum and the balance nickel.

    摘要翻译： 用于保护基材免受高温氧化和热腐蚀环境的金属涂层，其包含约2.5至约13.5wt。 ％钴，约12至约27wt。 约5至约7wt。％的铬。 ％铝，约0.0至约1.0wt。 ％钇，约0.0至约1.0wt。 ％铪，约1.0至约3.0wt。 ％硅，约0.0-约4.5wt。 ％钽，约0.0-约6.5wt。 ％钨，约0.0至约2.0重量％ ％铼，约0.0至约1.0wt。 钼和余量为镍。