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    SYSTEMS AND METHODS FOR MONITORING TURBINE COMPONENT STRAIN
    2.
    发明申请
    SYSTEMS AND METHODS FOR MONITORING TURBINE COMPONENT STRAIN 有权
    用于监测涡轮机组件应变的系统和方法

    公开(公告)号：US20160305769A1

    公开(公告)日：2016-10-20

    申请号：US14687158

    申请日：2015-04-15

    Applicant: General Electric Company

    Inventor： Jason Lee Burnside ,  Gregory Lee Hovis ,  Bryan J. Germann ,  John David Ward, Jr. ,  William F. Ranson

    IPC: G01B11/16

    CPC classification number: G01B11/165

    Abstract: Systems and methods for monitoring turbine component deformation are provided. The turbine component has an exterior surface. A method includes directly measuring a strain sensor configured on the exterior surface of the turbine component along an X-axis, a Y-axis and a Z-axis to obtain X-axis data points, Y-axis data points, and Z-axis data points. The X-axis, Y-axis and Z-axis are mutually orthogonal. The method further includes assembling a three-dimensional profile of the strain sensor based on the X-axis data points, Y-axis data points and Z-axis data points.

    Abstract translation: 提供了用于监测涡轮机组件变形的系统和方法。 涡轮机部件具有外表面。 一种方法包括直接测量沿着X轴，Y轴和Z轴在涡轮机部件的外表面上构造的应变传感器，以获得X轴数据点，Y轴数据点和Z轴 数据点。 X轴，Y轴和Z轴相互正交。 该方法还包括基于X轴数据点，Y轴数据点和Z轴数据点组装应变传感器的三维轮廓。

    Method for smut removal during stripping of coating
    4.
    发明授权
    Method for smut removal during stripping of coating 有权

    公开(公告)号：US10125425B2

    公开(公告)日：2018-11-13

    申请号：US13932394

    申请日：2013-07-01

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： John David Ward, Jr. ,  Liming Zhang

    IPC: C23G1/02 ,  C23F1/20 ,  C23F1/28 ,  C23F1/44 ,  C23G1/20 ,  F01D5/00

    Abstract: Stripping a metallic bond coat from an article using a wet chemical process. An article removed from service and having a metallic bond coat applied over a surface of its metallic substrate is provided. The metallic bond coat is used to improve the adhesion of a TBC to the article, so grit blasting to first remove any TBC applied over the bond coat and which still remains on the article initially may be required. The bond coated article is then immersed in an acid solution of HCl/H3PO4 at a predetermined temperature for a predetermined amount of time, the HCl/H3PO4 solution reacting with the bond coat applied over the metallic substrate to form a smut on the surface. The article is then removed from the HCl/H3PO4 solution and quickly immersed in a solution of NaOH for a predetermined amount of time to at least partially desmut the surface.

    METHOD FOR MODIFYING A AIRFOIL SHROUD AND AIRFOIL
    6.
    发明申请
    METHOD FOR MODIFYING A AIRFOIL SHROUD AND AIRFOIL 审中-公开
    用于修改空气动力飞溅和飞行器的方法

    公开(公告)号：US20140147283A1

    公开(公告)日：2014-05-29

    申请号：US13685950

    申请日：2012-11-27

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： John David Ward, Jr. ,  Kelvin Rono Aaron ,  James Ryan Connor ,  Melbourne James Myers ,  Brad Wilson VanTassel

    IPC: F01D5/00 ,  F01D5/22

    CPC classification number: F01D5/005 ,  F01D5/225 ,  F05D2230/80 ,  F05D2240/307 ,  F05D2260/94 ,  F05D2260/941 ,  F05D2270/332 ,  Y10T29/49234 ,  Y10T83/04

    Abstract: According to one aspect of the invention, a method is provided for modifying an airfoil shroud located at a tip of an airfoil of a airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut.

    Abstract translation: 根据本发明的一个方面，提供了一种用于修改位于翼型的翼型的尖端处的翼型护罩的方法，所述翼型护罩具有第一端边缘，第二端边缘，前缘和后缘。 该方法包括将参考位置定位在翼型护罩的第一端边缘中，参考位置靠近从基本水平的表面周向延伸的密封轨道，并在翼型护罩中形成浮雕切口以移除参考位置，其中修改 的翼型护罩在形成浮雕切割后完成。

    Fixture for an airfoil shroud and method for modifying an airfoil shroud
    7.
    发明授权
    Fixture for an airfoil shroud and method for modifying an airfoil shroud 有权
    用于翼型护罩的夹具和用于修改翼型护罩的方法

    公开(公告)号：US09567860B2

    公开(公告)日：2017-02-14

    申请号：US13685943

    申请日：2012-11-27

    Applicant: General Electric Company

    Inventor： Jacob Andrew Salm ,  James Ryan Connor ,  John David Ward, Jr.

    IPC: B25B11/00 ,  F01D5/22 ,  B23P6/00 ,  F01D5/00

    CPC classification number: F01D5/225 ,  B23P6/002 ,  F01D5/005 ,  F05D2260/94 ,  F05D2270/332 ,  Y10T29/49318

    Abstract: According to one aspect, a fixture for an airfoil shroud having a first end edge, a second end edge, a leading edge, a trailing edge, a radially outer side and a radially inner side with respect to a rotor axis of a bucket having the airfoil shroud is provided. The fixture includes a base plate, a first member extending from the base plate configured to locate and abut the first end edge, a second member extending from the base plate configured to locate and abut a side of a seal rail, a third member extending from the base plate configured to locate and abut the radially outer side of the airfoil shroud and a template recess formed in the base plate proximate the first end edge to define a geometry of a relief cut in the trailing edge of the airfoil shroud.

    Abstract translation: 根据一个方面，一种用于翼型护罩的固定装置，具有相对于桶的转子轴线具有第一端边缘，第二端边缘，前缘，后缘，径向外侧和径向内侧， 提供翼型护罩。 所述固定装置包括基板，从所述基板延伸的第一构件，所述第一构件被构造成定位和邻接所述第一端边缘;第二构件，其从所述基板延伸，所述第二构件从所述基板延伸，所述第二构件被构造成定位和邻接密封轨的侧面;第三构件， 所述基板被构造成定位并邻接所述翼型件护罩的径向外侧，以及形成在靠近所述第一端边缘的所述基板中的模板凹部，以限定在所述翼型件护罩的后缘中切割的浮雕的几何形状。

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