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    IN SITU TIP REPAIR OF AN AIRFOIL TIP IN A GAS TURBINE ENGINE VIA FRICTIONAL WELDING
    2.
    发明公开
    IN SITU TIP REPAIR OF AN AIRFOIL TIP IN A GAS TURBINE ENGINE VIA FRICTIONAL WELDING 审中-公开
    气体涡轮发动机翼型尖端的摩擦焊接原位修复

    公开(公告)号：EP3213865A1

    公开(公告)日：2017-09-06

    申请号：EP17158351.1

    申请日：2017-02-28

    申请人： General Electric Company

    发明人： DIWINSKY, David Scott ,  ROBERTS, Herbert Chidsey

    IPC分类号： B23P6/00 ,  F01D5/00 ,  F01D25/28 ,  B23K20/12 ,  B25B5/06

    CPC分类号： F01D5/005 ,  B23K20/1215 ,  B23K20/129 ,  B23K2101/001 ,  B23P6/005 ,  F01D5/30 ,  F01D25/285 ,  F05D2220/32 ,  F05D2230/239 ,  F05D2230/80

    摘要： Methods for material build-up on a tip 69 of a blade 68 of a gas turbine engine 10 are provided. The method can include inserting a material supply 102 and an inflatable bladder 100 between the tip 69 and a shroud 76 such that the material supply 102 is exposed to the tip 69 and the inflatable bladder 100 is positioned between the material supply 102 and a shroud 76, inflating the inflatable bladder 100 to force contact between the material supply 102 and the tip 69, and causing relative movement between the material supply 100 and the tip 69. The relative movement, in combination with the radial biased contact between the material supply 102 and the tip 69, creates heat through friction. As such, the relative movement can frictionally weld new material from the material supply 102 onto the tip 69 of the blade 68. For example, the heat created can be sufficient to melt the surface of the material supply 102 to transfer material from the material supply 102 to the tip 69.

    摘要翻译： 提供了用于在燃气涡轮发动机10的叶片68的尖端69上积聚材料的方法。 该方法可包括将材料供应102和可膨胀囊100插入尖端69和护罩76之间，使得材料供应102暴露于尖端69，并且可膨胀囊100定位在材料供应102和护罩76之间 ，使可膨胀囊状物100膨胀以迫使材料供应装置102与尖端69之间接触，并引起材料供应装置100与尖端69之间的相对运动。相对运动与材料供应装置102和 尖端69通过摩擦产生热量。 这样，相对运动可以摩擦地将来自材料供应装置102的新材料焊接到刀片68的尖端69上。例如，所产生的热量可以足以熔化材料供应装置102的表面以将材料从材料供应装置 102到尖端69。

    GAS TURBINE IN SITU INFLATABLE BLADDERS FOR ON-WING REPAIR
    5.
    发明公开
    GAS TURBINE IN SITU INFLATABLE BLADDERS FOR ON-WING REPAIR 审中-公开
    燃气涡轮机用于翼上维修的原位充气式鼓风机

    公开(公告)号：EP3222751A1

    公开(公告)日：2017-09-27

    申请号：EP17162176.6

    申请日：2017-03-21

    申请人： General Electric Company

    发明人： DIWINSKY, David Scott ,  ROBERTS, Herbert Chidsey

    IPC分类号： C23C28/00 ,  C23C30/00 ,  B23P6/00 ,  F01D5/00

    CPC分类号： F01D25/285 ,  B23P6/002 ,  C23C4/01 ,  C23C4/02 ,  C23C16/50 ,  F01D5/005 ,  F01D9/041 ,  F05D2220/323 ,  F05D2230/80 ,  F05D2230/90 ,  Y02T50/6765

    摘要： Methods are provided for repairing a surface of a component 204 within a gas turbine engine 10. A first bladder 100 and a second bladder 200 can be installed (simultaneously or independently) within the gas turbine engine 10. The first bladder 100 and the second bladder 200 can then be inflated with an inflating fluid to form a first circumferential seal and a second circumferential seal to define an isolated area within the gas turbine engine 10. All the surfaces within the isolated area can then be coated with a masking layer 306. At least a portion of the masking layer 306 can then be removed to expose a working area, and a coating can be formed on the working area.

    摘要翻译： 提供了用于修理燃气涡轮发动机10内的部件204的表面的方法。第一囊袋100和第二囊袋200可以（同时或独立地）安装在燃气涡轮发动机10内。第一囊袋100和第二囊袋 200然后可以用充气流体充气以形成第一周向密封件和第二周向密封件以限定燃气涡轮发动机10内的隔离区域。然后，隔离区域内的所有表面可以涂覆有掩模层306.在 然后可以移除掩模层306的至少一部分以暴露工作区域，并且可以在工作区域上形成涂层。

    SYSTEM FOR REPAIRING A BEND IN A TURBINE BLADE OF A TURBINE OF A GAS TURBINE ENGINE AND CORRESPONDING METHOD FOR REPAIRING
    6.
    发明公开
    SYSTEM FOR REPAIRING A BEND IN A TURBINE BLADE OF A TURBINE OF A GAS TURBINE ENGINE AND CORRESPONDING METHOD FOR REPAIRING 审中-公开
    用于修复汽轮机涡轮叶片中的弯曲的系统和用于修复的相应方法

    公开(公告)号：EP3208418A1

    公开(公告)日：2017-08-23

    申请号：EP17156142.6

    申请日：2017-02-14

    申请人： General Electric Company

    发明人： ROBERTS, Herbert Chidsey ,  DIWINSKY, David Scott

    IPC分类号： F01D5/00 ,  B23P6/00 ,  B21D3/16

    CPC分类号： F01D5/005 ,  B21D3/16 ,  B23P6/002 ,  F01D5/02 ,  F01D5/12 ,  F01D25/285 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/307

    摘要： The present disclosure is directed to an improved system and method for repairing a bend in a turbine blade of a turbine of a gas turbine engine (10). The system includes an articulating guide configured to fit into an access port of the turbine. The articulating guide (114) includes a proximal end (116) and a distal end (118). The system also includes a repair tool (112) configured at the distal end (118) of the articulating guide (114). Further, the repair tool (112) is configured to fit over the turbine blade. Thus, the repair tool (112) is configured to bend the turbine blade (112) to an unbent position while the turbine blade (112) is secured within the turbine.

    摘要翻译： 本公开涉及一种用于修理燃气涡轮发动机（10）的涡轮机的涡轮机叶片中的弯曲部的改进的系统和方法。 该系统包括配置成装配到涡轮机的进入端口中的关节式运动引导件。 铰接引导件（114）包括近端（116）和远端（118）。 该系统还包括配置在关节运动引导件（114）的远端（118）处的修理工具（112）。 此外，修理工具（112）构造成配合在涡轮叶片上。 因此，修理工具（112）构造成在涡轮机叶片（112）固定在涡轮机内的同时将涡轮机叶片（112）弯曲到未弯曲位置。

    Crack-resistant environmental barrier coatings
    7.
    发明公开
    Crack-resistant environmental barrier coatings 审中-公开
    Bruchfeste Umgebungssperrschichten

    公开(公告)号：EP2698446A2

    公开(公告)日：2014-02-19

    申请号：EP13180609.3

    申请日：2013-08-15

    申请人： General Electric Company

    发明人： ZHANG, James ,  ROBERTS, Herbert Chidsey ,  DAS, Rupak

    IPC分类号： C23C4/02 ,  C23C4/18 ,  C23C30/00 ,  C23C16/02 ,  C23C16/56

    CPC分类号： C23C4/02 ,  C04B41/009 ,  C04B41/52 ,  C04B41/89 ,  C23C4/18 ,  C23C16/02 ,  C23C16/56 ,  C23C30/00 ,  F01D5/288 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/125 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/307 ,  Y10T428/24793 ,  C04B35/565 ,  C04B35/806 ,  C04B41/5096 ,  C04B41/5059 ,  C04B41/522 ,  C04B41/5066 ,  C04B41/5024 ,  C04B41/5042

    摘要： Methods suitable for reducing corner cracking of environmental barrier coating systems (20). The methods include forming at least one layer of a first portion (22) of the environmental barrier coating system (20) on at least a first region of the component, performing a first heat treatment, forming at least one layer of a second portion (28) of the environmental barrier coating system (20) on a second region of the component, and performing a second heat treatment to the component. Edges of the first portion (36) and edges of the second portion (38) form an angle of at most 60° with respect to a surface of the first region of the component. During the second heat treatment, the second portion (28) of the EBC system expands and the expansion of the second portion (28) of the EBC system (20) is at least partially constrained by the first portion (22) of the EBC system (20) to reduce tensile interfacial stresses in the EBC system.

    摘要翻译： 适用于减少环境屏障涂层系统的角裂纹的方法（20）。 所述方法包括在至少部件的第一区域上形成至少一层环境阻挡涂层系统（20）的第一部分（22），进行第一热处理，形成至少一层第二部分（ 28）在所述部件的第二区域上的所述环境阻挡涂层系统（20），并且对所述部件执行第二热处理。 第一部分（36）的边缘和第二部分（38）的边缘相对于部件的第一区域的表面形成至多60°的角度。 在第二热处理期间，EBC系统的第二部分（28）膨胀并且EBC系统（20）的第二部分（28）的膨胀至少部分地被EBC系统的第一部分（22）约束 （20）以减少EBC系统中的拉伸界面应力。