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Patent Agency Ranking
1.发明申请公开(公告)号：US20160146014A1
公开(公告)日：2016-05-26
申请号：US14548656
申请日：2014-11-20
Applicant: General Electric Company
Inventor： James Ryan Connor , Robert Trent Hullender , Keith Alan Lord
CPC classification number: B23H9/10 , B23K26/342 , B23K2101/001 , B23P6/007 , F01D5/005 , F05D2230/31 , F05D2240/80
Abstract: Methods for modifying bucket platforms of turbine buckets include removing a portion of the bucket platform to form a void, wherein the void comprises a predetermined geometry, and adding a filler material in a plurality of layers to fill the void.
Abstract translation: 用于修改涡轮机铲斗的铲斗平台的方法包括移除铲斗平台的一部分以形成空隙，其中空隙包括预定几何形状，并且在多个层中加入填充材料以填充空隙。
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公开(公告)号：US09611753B2
公开(公告)日：2017-04-04
申请号：US14264202
申请日：2014-04-29
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Blake Allen Fulton , Keith Alan Lord
CPC classification number: F01D21/003 , F01D5/005 , F01D25/00 , F01D25/285 , F05D2260/80
Abstract: An apparatus for inspecting a turbine blade tip shroud includes a frame comprising a top surface and a bottom surface that is alignable with the turbine blade tip shroud, and, at least one z-notch inspection slot that passes through the frame from the top surface to the bottom surface and is positioned to align with at least one z-notch of the turbine blade tip shroud when the frame is aligned on the turbine blade tip shroud. The apparatus further includes a removable z-notch inspection insert comprising a cross-sectional profile substantially matching the at least one z-notch inspection slot and comprising a z-notch guide face that faces the z-notch of the turbine blade tip shroud when the removable z-notch inspection insert is passed through the z-notch inspection slot
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公开(公告)号：US20170044900A1
公开(公告)日：2017-02-16
申请号：US14824566
申请日：2015-08-12
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Mark Carmine Bellino , James Ryan Connor , Gareth William David Lewis , Keith Alan Lord
CPC classification number: F01D5/005 , B23P6/007 , F01D5/284 , F01D5/288 , F05D2220/30 , F05D2230/30 , F05D2230/80 , F05D2300/2261 , G05B15/02 , G05B19/4099 , G05B2219/35128 , G05B2219/45147
Abstract: A system for adaptively machining a shroud of a blade used in a turbomachine is provided. The system may include a computer system including a module(s) configured to: extract geometric location data from a 3D model of the shroud after use in the turbomachine, the 3D model created by digitizing using a digitizing device. The geometric location data includes geometric location data of a hard face plane of the shroud exposed to wear during turbomachine operation and of a non-worn surface adjacent to the hard face plane substantially unexposed to wear during turbomachine operation. Comparing the geometric location data of the non-worn surface from the three-dimensional model to a manufacturing model of the blade determines a change in position of the non-worn surface from use of the blade in the turbomachine. The change in position is used to modify a machining instruction used by a machining device to repair the hard face plane.
Abstract translation: 提供一种用于自动加工用于涡轮机中的叶片的护罩的系统。 该系统可以包括计算机系统，其包括被配置为：在使用涡轮机之后从护罩的3D模型中提取几何位置数据的模块，通过使用数字化装置进行数字化创建的3D模型。 几何位置数据包括在涡轮机操作期间暴露于磨损的护罩的硬面平面的几何位置数据和在涡轮机操作期间基本上未暴露于磨损的与硬面平面相邻的未磨损表面。 将来自三维模型的非磨损表面的几何位置数据与刀片的制造模型进行比较，确定在磨损机器中使用刀片时未磨损表面的位置的变化。 位置变化用于修改加工装置使用的加工指令来修复硬面平面。
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公开(公告)号：US09856734B2
公开(公告)日：2018-01-02
申请号：US14824566
申请日：2015-08-12
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Mark Carmine Bellino , James Ryan Connor , Gareth William David Lewis , Keith Alan Lord
IPC: F01D5/00 , G05B19/4099 , G05B15/02 , B23P6/00
CPC classification number: F01D5/005 , B23P6/007 , F01D5/284 , F01D5/288 , F05D2220/30 , F05D2230/30 , F05D2230/80 , F05D2300/2261 , G05B15/02 , G05B19/4099 , G05B2219/35128 , G05B2219/45147
Abstract: A system for adaptively machining a shroud of a blade used in a turbomachine is provided. The system may include a computer system including a module(s) configured to: extract geometric location data from a 3D model of the shroud after use in the turbomachine, the 3D model created by digitizing using a digitizing device. The geometric location data includes geometric location data of a hard face plane of the shroud exposed to wear during turbomachine operation and of a non-worn surface adjacent to the hard face plane substantially unexposed to wear during turbomachine operation. Comparing the geometric location data of the non-worn surface from the three-dimensional model to a manufacturing model of the blade determines a change in position of the non-worn surface from use of the blade in the turbomachine. The change in position is used to modify a machining instruction used by a machining device to repair the hard face plane.
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公开(公告)号：US20150308284A1
公开(公告)日：2015-10-29
申请号：US14264202
申请日：2014-04-29
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Blake Allen Fulton , Keith Alan Lord
CPC classification number: F01D21/003 , F01D5/005 , F01D25/00 , F01D25/285 , F05D2260/80
Abstract: An apparatus for inspecting a turbine blade tip shroud includes a frame comprising a top surface and a bottom surface that is alignable with the turbine blade tip shroud, and, at least one z-notch inspection slot that passes through the frame from the top surface to the bottom surface and is positioned to align with at least one z-notch of the turbine blade tip shroud when the frame is aligned on the turbine blade tip shroud. The apparatus further includes a removable z-notch inspection insert comprising a cross-sectional profile substantially matching the at least one z-notch inspection slot and comprising a z-notch guide face that faces the z-notch of the turbine blade tip shroud when the removable z-notch inspection insert is passed through the z-notch inspection slot
Abstract translation: 一种用于检查涡轮叶片尖端护罩的装置包括框架，该框架包括可与涡轮机叶片护罩对准的顶表面和底表面，以及至少一个Z形切口检查槽，其通过框架从顶表面到 所述底表面定位成当所述框架对准所述涡轮叶片尖端护罩时与所述涡轮机叶片梢罩的至少一个z形切口对准。 所述装置还包括可拆卸的Z形切口检查插入件，其包括基本上匹配所述至少一个z形切口检查狭槽的横截面轮廓，并且包括当所述涡轮叶片尖端护罩的Z形凹口面对时，Z形切口引导面 可移动的Z形缺口检查刀片通过z形缺口检查槽
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