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公开(公告)号：US20170167930A1
公开(公告)日：2017-06-15
申请号：US14964816
申请日：2015-12-10
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Thomas James Batzinger , Bryan Joseph Germann , John David Ward, JR. , William Farris Ranson
CPC classification number: G01L1/25 , C23C28/321 , C23C28/3455 , F01D5/288 , F01D9/02 , F01D17/02 , F01D25/005 , F05D2270/808 , F05D2300/611 , G01B15/00 , G01B15/06 , G01M15/14
Abstract: Components can comprise a substrate, an embedded strain sensor comprising at least two reference points disposed on the substrate, and an outer coating disposed over at least a portion of the embedded strain sensor.
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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：US20170148152A1
公开(公告)日：2017-05-25
申请号：US14951669
申请日：2015-11-25
Applicant: General Electric Company
Inventor： Bryan J. Germann , Gregory Lee Hovis , Jacob Andrew Salm
CPC classification number: H04N5/2256 , G01B11/165 , G01B11/24 , G01M15/14 , G06T7/60 , G06T7/70 , G06T2200/04 , G06T2207/30204
Abstract: A system for monitoring a component is provided. The system includes a plurality of fiducial markers, an optical scanner for analyzing the fiducial markers, and a processor. The plurality of fiducial markers may be on an exterior surface of the component. The processor may be in operable communication with the optical scanner and operable for measuring the fiducial markers along an X-axis, a Y-axis, and a Z-axis to obtain an X-axis data point set, a Y-axis data point set, and a Z-axis data point set. The X-axis, the Y-axis, and the Z-axis are mutually orthogonal. Methods of using the system are also provided.
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5.发明授权公开(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.
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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Patent Agency Ranking
公开(公告)号：US09434017B2
公开(公告)日：2016-09-06
申请号：US14318956
申请日：2014-06-30
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Srikanth Chandrudu Kottilingam , Jonathan Matthew Lomas , Gareth William David Lewis , Cem Murat Eminoglu
CPC classification number: B23K1/0018 , B23K1/19 , B23K35/0244 , B23K35/3046 , B23K2101/001 , C22C19/002 , F01D5/147 , F01D5/225 , F05D2230/22 , F05D2230/237 , Y02T50/671
Abstract: Braze methods include providing a substrate comprising a pre-sintered preform disposed thereon, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy. Braze methods further include at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform, and heating the pre-sintered preform on the substrate.
Abstract translation: 钎焊方法包括提供包括预先设置在其上的预烧结预成型件的基材，其中预烧结预成型件包括含有约30重量％至约90重量％混合物的基础合金的混合物，以及包含足量的 熔点低于基体合金的熔点。 钎焊方法还包括用耐热材料至少部分地覆盖预烧结的预成型件，其中耐热材料的熔融温度高于预烧结预制件的熔融温度，并且将预烧结的预制件加热到 基质。
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公开(公告)号：US20150375322A1
公开(公告)日：2015-12-31
申请号：US14318956
申请日：2014-06-30
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Srikanth Chandrudu Kottilingam , Jonathan Matthew Lomas , Gareth William David Lewis , Cem Murat Eminoglu
CPC classification number: B23K1/0018 , B23K1/19 , B23K35/0244 , B23K35/3046 , B23K2101/001 , C22C19/002 , F01D5/147 , F01D5/225 , F05D2230/22 , F05D2230/237 , Y02T50/671
Abstract: Braze methods include providing a substrate comprising a pre-sintered preform disposed thereon, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy. Braze methods further include at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform, and heating the pre-sintered preform on the substrate.
Abstract translation: 钎焊方法包括提供包括预先设置在其上的预烧结预成型件的基材，其中预烧结预成型件包括含有约30重量％至约90重量％的混合物的基础合金的混合物，以及包含足量的 熔点低于基体合金的熔点。 钎焊方法还包括用耐热材料至少部分地覆盖预烧结的预成型件，其中耐热材料的熔融温度高于预烧结预制件的熔融温度，并且将预烧结的预制件加热到 基质。
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公开(公告)号：US20170176291A1
公开(公告)日：2017-06-22
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
IPC: G01M15/14
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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公开(公告)号：US20170159446A1
公开(公告)日：2017-06-08
申请号：US14956641
申请日：2015-12-02
Applicant: General Electric Company
Inventor： Jonathan William Graham , Paul Michael Kienitz , Jacob Andrew Salm
CPC classification number: F01D5/147 , F01D5/225 , F05D2220/31 , F05D2240/307 , F05D2260/80 , F05D2260/83
Abstract: A turbine engine system includes a component positioned such that the component is subject to wear. The component includes an outer surface configured to be subjected to wear and a wear indication feature formed in the outer surface. The wear indication feature includes a first dimension at the outer surface and a second dimension at an inward location relative to the outer surface. The second dimension is different from the first dimension.
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公开(公告)号：US20150132127A1
公开(公告)日：2015-05-14
申请号：US14077873
申请日：2013-11-12
Applicant: General Electric Company
Inventor： Jacob Andrew Salm , Kelsey Elizabeth Beach , Alexander James Pistner , Birol Turan
IPC: F01D21/00
CPC classification number: F01D21/003 , G01B11/24 , G01M5/0016 , G01M5/0033 , G01M5/0075
Abstract: A system may include at least one computer device configured to attain a two-dimensional used profile of a leading edge at a specified radial position on a turbomachine airfoil after use. The system aligns opposing substantially straight alignment portions of the two-dimensional used profile with opposing substantially straight alignment portions of a previously attained, two-dimensional, baseline profile of the turbomachine airfoil. The alignment portions of each profile are in substantially identical radial locations of the turbomachine airfoil. Comparing the used profile to the baseline profile determines whether the leading edge at the specified radial position of the used turbomachine airfoil has erosion. The system may also include a laser profiler for measuring the turbomachine airfoil.
Abstract translation: 系统可以包括至少一个计算机设备，其被配置为在使用后获得在涡轮机翼型上的指定径向位置处的前缘的二维使用轮廓。 系统将二维使用轮廓的相对的基本上直的对准部分对准涡轮机翼型的先前达到的二维基线轮廓的相对的基本上直的对准部分。 每个型材的对准部分位于涡轮机翼型件的基本相同的径向位置。 将使用的轮廓与基线轮廓进行比较确定在使用的涡轮机翼型的指定径向位置处的前缘是否具有侵蚀。 该系统还可以包括用于测量涡轮机翼型的激光轮廓仪。
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