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11.发明申请公开(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.
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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公开(公告)号：US10024760B2
公开(公告)日：2018-07-17
申请号：US14972202
申请日：2015-12-17
Applicant: General Electric Company
Inventor： Parvangada Ganapathy Bojappa , Jason Lee Burnside , Gregory Lee Hovis , William Farris Ranson , Jacob Andrew Salm
Abstract: Methods for monitoring a components include locating a plurality of machined surface features on the component, locating at least one reference point, and measuring a plurality of first distances between the plurality of machined surface features and the at least one reference point.
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Patent Agency Ranking
公开(公告)号：US10013752B2
公开(公告)日：2018-07-03
申请号：US15355202
申请日：2016-11-18
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Onat Bas , Birol Turan
CPC classification number: G06T7/0004 , F01D5/005 , F01D5/225 , F01D21/003 , F05D2260/80 , F05D2260/81 , F05D2270/80 , G01B11/002 , G01B11/16 , G01B21/16 , G01N21/8851 , G01N2201/12 , G06T7/60 , G06T7/70 , G06T19/20 , G06T2200/04 , G06T2200/08 , G06T2207/30164 , G06T2219/2004
Abstract: A system and method for virtually inspecting a blade stage is disclosed. The system may include a digitizing device for obtaining a three-dimensional model of a shroud of each blade of the blade stage. A computer system may include at least one module configured to perform the following processes: extract a geometric location data of a plurality of reference points of each shroud from a three-dimensional model of a shroud of each blade of the blade stage created by digitizing using a digitizing device; generate a 3D virtual rendering of the shrouds of the blade stage based on the geometric location data and the known dimensions of the blade stage, the three-dimensional virtual rendering including a rendering of the plurality of reference points of each shroud; and inspect the blade stage using the three-dimensional virtual rendering.
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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：US09542739B1
公开(公告)日：2017-01-10
申请号：US14824464
申请日：2015-08-12
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , James Ryan Connor , Jeffrey David Erno
CPC classification number: G06T19/20 , F01D5/005 , F01D5/225 , F05D2260/80 , F05D2260/81 , G01B21/16 , G06T19/00
Abstract: A system and method for virtually inspecting contact gaps of a blade stage of a turbomachine is disclosed. The system may include a digitizing device for obtaining a three-dimensional model of a shroud of each blade of the blade stage. A computer system may include at least one module configured to perform the following steps: extracting a geometric location data of a hard place plane of each shroud from the three-dimensional model; generating a three-dimensional virtual rendering of the shrouds of the blade stage based on the geometric location data and the known dimensions of the blade stage, the three-dimensional virtual rendering including a rendering of contact gaps between adjacent shrouds; and inspecting the blade stage using the three-dimensional virtual rendering.
Abstract translation: 公开了一种用于虚拟检查涡轮机的叶片级的接触间隙的系统和方法。 系统可以包括用于获得叶片台的每个叶片的护罩的三维模型的数字化装置。 计算机系统可以包括被配置为执行以下步骤的至少一个模块：从三维模型中提取每个护罩的硬地平面的几何位置数据; 基于所述几何位置数据和所述叶片级的已知尺寸产生所述叶片台的所述护罩的三维虚拟渲染，所述三维虚拟渲染包括相邻护罩之间的接触间隙的渲染; 并使用三维虚拟渲染来检查刀片台。
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公开(公告)号：US20150377037A1
公开(公告)日：2015-12-31
申请号：US14318977
申请日：2014-06-30
Applicant: General Electric Company
CPC classification number: B23K35/3046 , B23K1/0018 , B23K1/008 , B23K1/19 , B23K1/206 , B23K35/0222 , B23K35/0244 , B23K35/0255 , B23K35/30 , B23K35/3033 , B23K2101/001 , B23K2103/26 , B23P6/005 , B23P15/04 , C23C4/00 , C23C4/129 , F01D5/147 , F01D5/225 , F05D2230/22 , Y02T50/671
Abstract: Braze methods for turbine buckets include providing the turbine bucket comprising a modification surface, wherein the modification surface comprises a non-z-notch contact surface, disposing a pre-sintered preform on the modification surface and, heating the pre-sintered preform on the modification surface to bond the pre-sintered preform to the turbine bucket at the modification surface.
Abstract translation: 用于涡轮机桶的钎焊方法包括提供包括改性表面的涡轮机桶，其中改性表面包括非Z形切口接触表面，将预烧结的预制件设置在改性表面上，以及在修饰表面上加热预烧结的预制件 表面，以将预烧结的预制件结合到修饰表面处的涡轮机桶。
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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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