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    FIXTURE FOR AN AIRFOIL SHROUD AND METHOD FOR MODIFYING AN AIRFOIL SHROUD
    1.
    发明申请
    FIXTURE FOR AN AIRFOIL SHROUD AND METHOD FOR MODIFYING AN AIRFOIL SHROUD 有权
    一种空气压缩机的装置以及修改空气压缩机的方法

    公开(公告)号：US20140147285A1

    公开(公告)日：2014-05-29

    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: F01D5/22 ,  B23P6/00

    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。

    BUCKET TIP SHROUD MEASUREMENT FIXTURE AND METHOD OF MEASURING BUCKET TIP SHROUD ORIENTATION
    3.
    发明申请
    BUCKET TIP SHROUD MEASUREMENT FIXTURE AND METHOD OF MEASURING BUCKET TIP SHROUD ORIENTATION 有权
    BUCKET TIP SHROUD测量仪器和测量BUCKET TIP SHROUD方位的方法

    公开(公告)号：US20150128433A1

    公开(公告)日：2015-05-14

    申请号：US14076558

    申请日：2013-11-11

    Applicant: General Electric Company

    Inventor： John David Ward, JR. ,  Juan Pablo Cilia ,  James Ryan Connor ,  Jason Adam Neville ,  Christopher Allen Nafis ,  Neil Robert Peddar ,  Antonio Rodriguez ,  Daniel Howard Tragesser

    IPC: G01B5/008

    CPC classification number: G01B5/008 ,  F01D11/00 ,  F01D25/285 ,  F05D2260/83 ,  G01B5/0002 ,  G01B5/0004 ,  G01B5/205

    Abstract: A bucket tip shroud measurement fixture includes a frame extending from a first end to a second end through an intermediate portion having a first surface and an opposing second surface, a first tip shroud fixing member extending from the second surface of the frame at the first end, and a second tip shroud fixing member extending from the second surface of the frame at the second end. The first and second tip shroud fixing members are configured and disposed to retain and establish an orientation of a bucket tip shroud relative the frame. A plurality of reference points are provided on the frame. The plurality of reference points are configured and disposed to receive a coordinate measuring machine (CMM) probe.

    Abstract translation: 铲斗顶部护罩测量夹具包括：框架，其从第一端延伸到第二端，通过具有第一表面和相对的第二表面的中间部分;第一末端护罩固定件，在第一端从框架的第二表面延伸; 以及在第二端处从框架的第二表面延伸的第二顶端罩固定构件。 第一和第二末端罩固定构件被构造和设置成保持并建立相对于框架的铲斗顶部护罩的取向。 在框架上设置多个参考点。 多个参考点被配置和设置成接收坐标测量机（CMM）探针。

    METHODS FOR DETERMINING STRAIN ON TURBINE COMPONENTS USING A PLURALITY OF STRAIN SENSOR REFERENCE FEATURES
    4.
    发明申请
    METHODS FOR DETERMINING STRAIN ON TURBINE COMPONENTS USING A PLURALITY OF STRAIN SENSOR REFERENCE FEATURES 有权
    使用多种应变传感器参考特征确定涡轮机组件应变的方法

    公开(公告)号：US20160252417A1

    公开(公告)日：2016-09-01

    申请号：US14633557

    申请日：2015-02-27

    Applicant: General Electric Company

    Inventor： Gregory Lee Hovis ,  John David Ward, JR. ,  William Farris Ranson

    IPC: G01L5/16

    CPC classification number: G01M5/0016 ,  G01M5/005 ,  G01M5/0091

    Abstract: Methods for determining strain on turbine components include providing a turbine component comprising a plurality of strain sensor reference features disposed along the turbine component separated from one another by a plurality of first distances at a first time, reading the plurality of strain sensor reference features at a second time to determine a plurality of second distances between the plurality of strain sensor reference features, and comparing the plurality of second distances to the plurality of first distances to determine a plurality of non-linear strain measurements between the plurality of strain sensor reference features.

    Abstract translation: 用于确定涡轮机部件上的应变的方法包括提供涡轮机部件，其包括沿着涡轮部件设置的多个应变传感器参考特征，所述多个应变传感器参考特征在第一时间彼此分离多个第一距离，在第一时间读取多个应变传感器参考特征 第二次确定所述多个应变传感器参考特征之间的多个第二距离，以及将所述多个第二距离与所述多个第一距离进行比较，以确定所述多个应变传感器参考特征之间的多个非线性应变测量。

    TURBOMACHINE COMPONENT MONITORING SYSTEM AND METHOD
    6.
    发明申请
    TURBOMACHINE COMPONENT MONITORING SYSTEM AND METHOD 审中-公开
    涡轮组件监测系统和方法

    公开(公告)号：US20140267677A1

    公开(公告)日：2014-09-18

    申请号：US13829052

    申请日：2013-03-14

    Applicant: General Electric Company

    Inventor： John David Ward, JR. ,  Thomas James Batzinger ,  Jamison William Janawitz ,  Christopher Edward Thompson

    IPC: G06T7/00 ,  G02B23/24

    CPC classification number: G06T7/0004 ,  G01M5/0016 ,  G01M5/0033 ,  G01M5/0091 ,  G02B23/2484

    Abstract: Various embodiments include approaches for monitoring turbomachine components. In various particular embodiments, a system for monitoring a component within a turbomachine includes: a borescope probe sized to pass through an opening in the turbomachine, the borescope probe for detecting a symbolic data array on the component within the turbomachine; and at least one computing device operably coupled to the borescope probe, the at least one computing device configured to: obtain image data about the symbolic data array from the borescope probe; evaluate the image data to determine whether the image data is compatible with a symbolic data array analysis program; and analyze the image data using the symbolic data array analysis program in response to determining the image data is compatible with the symbolic data array analysis program.

    Abstract translation: 各种实施例包括用于监测涡轮机组件的方法。 在各种具体实施例中，用于监测涡轮机内的部件的系统包括：尺寸适于穿过涡轮机中的开口的管道探针探针，用于检测涡轮机内的部件上的符号数据阵列的管道探针; 以及至少一个计算设备，其可操作地耦合到所述管道探针，所述至少一个计算设备被配置为：从所述管道探针获得关于所述符号数据阵列的图像数据; 评估图像数据以确定图像数据是否与符号数据阵列分析程序兼容; 并且响应于确定图像数据与符号数据阵列分析程序兼容，使用符号数据阵列分析程序来分析图像数据。

    COMPONENT IDENTIFICATION SYSTEM
    9.
    发明申请
    COMPONENT IDENTIFICATION SYSTEM 有权
    组件识别系统

    公开(公告)号：US20140306003A1

    公开(公告)日：2014-10-16

    申请号：US13863209

    申请日：2013-04-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Shyamanth Kotian ,  Srivatsa Dhanvantri ,  John David Ward, JR.

    IPC: G06F17/30 ,  G06K7/14 ,  G01N21/95

    CPC classification number: G06F17/30 ,  F01D21/003 ,  F05D2230/72 ,  F05D2260/83 ,  G01N21/95 ,  G02B23/24 ,  G06K7/1417 ,  G06Q10/06 ,  G06Q10/08 ,  G06Q50/28

    Abstract: A component identification system for identifying an industrial machine component in situ is disclosed herein. In an embodiment, a computer system is provided which is configured to implement a method of identifying a component of an industrial machine in situ. In particular, the computer system is configured to decode an image containing a data matrix code, and identify the data matrix code in the image. The computer system is further configured to associate the data matrix code in the image with an identified component in a database.

    Abstract translation: 本文公开了用于识别原位工业机器部件的部件识别系统。 在一个实施例中，提供了一种计算机系统，其被配置为实现现场识别工业机器的部件的方法。 特别地，计算机系统被配置为对包含数据矩阵代码的图像进行解码，并且识别图像中的数据矩阵代码。 计算机系统还被配置为将图像中的数据矩阵代码与数据库中的识别的组件相关联。

    METHOD FOR MODIFYING AN AIRFOIL SHROUD
    10.
    发明申请
    METHOD FOR MODIFYING AN AIRFOIL SHROUD 审中-公开
    修改空气动力学风险的方法

    公开(公告)号：US20140147284A1

    公开(公告)日：2014-05-29

    申请号：US14046417

    申请日：2013-10-04

    Applicant: General Electric Company

    Inventor： John David Ward, JR. ,  Antonio Rodriguez ,  Jason Adam Neville

    IPC: F01D5/00 ,  F01D5/22

    CPC classification number: F01D5/005 ,  F01D5/16 ,  F01D5/225 ,  F01D11/12 ,  F05D2230/80 ,  F05D2240/307 ,  F05D2260/94 ,  F05D2260/96 ,  F05D2270/332 ,  Y10T29/49233 ,  Y10T83/04 ,  Y10T83/0524

    Abstract: A turbine engine, bucket and method for modifying an airfoil shroud of turbine bucket is disclosed. A reference location is located in a second end edge of the airfoil shroud proximate a seal rail of the airfoil shroud. A relief cut is formed in the airfoil shroud to remove the reference location. Additionally, another reference location may be located in a first end edge of the airfoil shroud proximate the seal rail. Another relief cut may be formed in the airfoil shroud to remove the other reference location.

    Abstract translation: 公开了一种涡轮发动机，铲斗和用于改变涡轮机叶片翼型护罩的方法。 参考位置位于靠近翼型护罩的密封轨道的翼型护罩的第二端边缘中。 在翼型护罩中形成浮雕切口以去除参考位置。 此外，另一个参考位置可以位于靠近密封轨道的翼型护罩的第一端边缘中。 可以在翼型护罩中形成另一个减压切口以移除另一个参考位置。

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