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    Turbine nozzle segment and method of repairing same
    2.
    发明公开
    Turbine nozzle segment and method of repairing same 有权
    的涡轮机和方法来修复这一

    公开(公告)号：EP1227218A3

    公开(公告)日：2004-01-02

    申请号：EP02250504.4

    申请日：2002-01-25

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Grady, Wayne Ray

    IPC分类号： F01D9/04 ,  B23P6/00 ,  F01D5/00

    CPC分类号： B23P6/002 ,  F01D5/005 ,  F01D9/04 ,  F01D9/044 ,  F05D2230/80 ,  Y02T50/67 ,  Y10T29/49336

    摘要： A method for repairing a turbine nozzle segment having at least two vanes disposed between outer and inner bands (14,16) includes separating the outer and inner bands (14,16) from the vanes, and forming one slot (36) for each vane through the outer band (14) and one slot for each vane through the inner band (16). A newly manufactured replacement vane (38) is provided for each one of the original vanes. Each replacement vane (38) has an outer boss (48) formed on an outer end thereof and an inner boss formed on an inner end (46) thereof. Then, each outer boss (48) is inserted into a corresponding one of the outer band slots (36), and each inner boss is inserted into a corresponding one of the inner band slots. Once the parts are so assembled, each outer boss (48) is welded to the outer band (14) on the cold side (18), and each inner boss is welded to the inner band (16) on the cold side (24). Each replacement vane (38) is also brazed to the outer and inner bands (14,16) on the respective hot sides (20, 26) thereof.

    Turbine nozzle segment and method of repairing same
    6.
    发明公开
    Turbine nozzle segment and method of repairing same 审中-公开
    涡轮喷嘴部分及其修理方法

    公开(公告)号：EP2412930A3

    公开(公告)日：2018-01-24

    申请号：EP11175241.6

    申请日：2011-07-25

    申请人： General Electric Company

    发明人： Garza, Jose Abiel ,  Grady, Wayne Ray ,  Mankowski, Pawel ,  Zak, Marcin ,  Trajer, Marcin

    IPC分类号： F01D9/04 ,  F01D5/22

    CPC分类号： F01D9/04 ,  F01D5/005 ,  F01D5/22 ,  F05D2230/80 ,  F05D2240/12 ,  Y02T50/67 ,  Y02T50/673 ,  Y10T29/49318

    摘要： A method is provided for repairing a metallic turbine component (18) which includes at least two airfoils (20) interconnected by a mid-span shroud (38). The method includes: (a) applying a reinforcement plate (40) to the mid-span shroud; (b) applying braze material (64) to at least a portion of a perimeter of the reinforcement plate; (c) heating the component to melt and flow the braze material between the reinforcement plate and the mid-span shroud; and (d) allowing the braze material to cool and solidify so as to bond the reinforcement plate to the mid-span shroud.

    摘要翻译： 提供了一种用于修理金属涡轮机部件（18）的方法，该金属涡轮机部件（18）包括由中跨度护罩（38）互连的至少两个翼型件（20）。 该方法包括：（a）将加强板（40）施加到中跨度护罩; （b）将铜焊材料（64）施加到加强板的周边的至少一部分上; （c）加热所述部件以使所述铜焊材料在所述加强板和所述中跨度护罩之间熔化并流动; （d）使铜焊材料冷却并固化，以便将增强板结合到中跨度罩。

    Repair Method For TBC Coated Turbine Components
    8.
    发明公开
    Repair Method For TBC Coated Turbine Components 审中-公开
    TBC涂层涡轮部件的修理方法

    公开(公告)号：EP2191930A2

    公开(公告)日：2010-06-02

    申请号：EP09176677.4

    申请日：2009-11-20

    申请人： General Electric Company

    发明人： Gupta, Bhupendra Kumar ,  Grady, Wayne Ray ,  Garcia, Antoine Freitas

    IPC分类号： B23P6/00 ,  C23C4/02 ,  F01D5/00

    CPC分类号： B23P6/007 ,  B23P6/045 ,  C23C4/02 ,  C23C4/04 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/3455 ,  F01D5/005 ,  F05D2230/90 ,  Y10T29/49318

    摘要： A method is provided for repairing a metallic turbine component which includes a thermal barrier coating system including a metallic bond coat (22) and a ceramic top coat (24). The method includes: (a) removing the top coat (24) using a mechanical process; (b) partially stripping the metallic bond coat (22) from the component, such that substantially no material of the component is removed; (c) repairing at least one defect in the turbine component; (d) applying a new metallic bond coat (26', 28') to the turbine component; and (e) applying a new ceramic top coat (24) over the metallic bond coat (26', 28').

    摘要翻译： 提供了一种用于修复金属涡轮机部件的方法，该金属涡轮机部件包括具有金属结合层（22）和陶瓷顶层（24）的热障涂层系统。 该方法包括：（a）使用机械工艺去除顶部涂层（24）; （b）从所述部件上部分地剥离所述金属结合涂层（22），使得所述部件的材料基本上不被去除; （c）修理涡轮机部件中的至少一个缺陷; （d）将新的金属粘结涂层（26'，28'）施加到所述涡轮机部件; 和（e）在金属粘结涂层（26'，28'）上施加新的陶瓷顶涂层（24）。

    Turbine nozzle segment and method of repairing same
    9.
    发明公开
    Turbine nozzle segment and method of repairing same 审中-公开
    Turbinenleitschaufelsegment und Reparaturverfahrendafür

    公开(公告)号：EP2412930A2

    公开(公告)日：2012-02-01

    申请号：EP11175241.6

    申请日：2011-07-25

    申请人： General Electric Company

    发明人： Garza, Jose Abiel ,  Grady, Wayne Ray ,  Mankowski, Pawel ,  Zak, Marcin ,  Trajer, Marcin

    IPC分类号： F01D9/04

    CPC分类号： F01D9/04 ,  F01D5/005 ,  F01D5/22 ,  F05D2230/80 ,  F05D2240/12 ,  Y02T50/67 ,  Y02T50/673 ,  Y10T29/49318

    摘要： A method is provided for repairing a metallic turbine component (18) which includes at least two airfoils (20) interconnected by a mid-span shroud (38). The method includes: (a) applying a reinforcement plate (40) to the mid-span shroud; (b) applying braze material (64) to at least a portion of a perimeter of the reinforcement plate; (c) heating the component to melt and flow the braze material between the reinforcement plate and the mid-span shroud; and (d) allowing the braze material to cool and solidify so as to bond the reinforcement plate to the mid-span shroud.

    摘要翻译： 提供一种用于修理金属涡轮机部件（18）的方法，所述金属涡轮机部件（18）包括通过中跨护罩（38）互连的至少两个翼型件（20）。 该方法包括：（a）将加强板（40）施加到中跨护罩上; （b）将钎焊材料（64）施加到所述加强板的周边的至少一部分; （c）加热部件以熔化并在加强板和中跨护罩之间流动钎焊材料; 和（d）允许钎焊材料冷却和固化，以将加强板粘合到中跨护罩上。

    Turbine nozzle segment and method of repairing same
    10.
    发明公开
    Turbine nozzle segment and method of repairing same 有权
    Turbinenleitapparat und Methode，um diesen zu reparieren

    公开(公告)号：EP1227218A2

    公开(公告)日：2002-07-31

    申请号：EP02250504.4

    申请日：2002-01-25

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Grady, Wayne Ray

    IPC分类号： F01D9/04 ,  B23P6/00

    CPC分类号： B23P6/002 ,  F01D5/005 ,  F01D9/04 ,  F01D9/044 ,  F05D2230/80 ,  Y02T50/67 ,  Y10T29/49336

    摘要： A method for repairing a turbine nozzle segment having at least two vanes disposed between outer and inner bands (14,16) includes separating the outer and inner bands (14,16) from the vanes, and forming one slot (36) for each vane through the outer band (14) and one slot for each vane through the inner band (16). A newly manufactured replacement vane (38) is provided for each one of the original vanes. Each replacement vane (38) has an outer boss (48) formed on an outer end thereof and an inner boss formed on an inner end (46) thereof. Then, each outer boss (48) is inserted into a corresponding one of the outer band slots (36), and each inner boss is inserted into a corresponding one of the inner band slots. Once the parts are so assembled, each outer boss (48) is welded to the outer band (14) on the cold side (18), and each inner boss is welded to the inner band (16) on the cold side (24). Each replacement vane (38) is also brazed to the outer and inner bands (14,16) on the respective hot sides (20, 26) thereof.

    摘要翻译： 一种用于修复涡轮喷嘴段的方法，其具有设置在外带和内带（14,16）之间的至少两个叶片，包括将外带和内带（14,16）与叶片分开，并为每个叶片形成一个槽（36） 通过外带（14）和通过内带（16）的每个叶片的一个槽。 为每个原始叶片设置新制造的替换叶片（38）。 每个更换叶片（38）具有形成在其外端上的外凸台（48）和形成在其内端（46）上的内凸台。 然后，将每个外凸台（48）插入对应的一个外带槽（36），并将每个内凸台插入相应的一个内带槽。 一旦部件被组装好，每个外凸台（48）就被焊接到冷侧（18）上的外带（14）上，并且每个内凸台焊接到冷侧（24）上的内带（16） 。 每个替换叶片（38）也钎焊到其相应的热侧（20,26）上的外带和内带（14,16）。