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公开(公告)号：US10001013B2
公开(公告)日：2018-06-19
申请号：US14198659
申请日：2014-03-06
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , James Ryan Connor , Bryan David Lewis , Adebukola Oluwaseun Benson
CPC classification number: F01D5/082 , B23P15/02 , F01D5/187 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/201 , Y02T50/676 , Y10T29/49341
Abstract: Platform cooling arrangements in a turbine rotor blade include a feedhole that extends from the suction side slash face to the interior cooling passage, and, one or more branch holes that each extends from the feedhole to the suction side slash face such that coolant flows from the interior cooling passage, through the feedhole to the one or more branch holes and exits the platform along the suction side slash face.
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2.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：US20160362988A1
公开(公告)日：2016-12-15
申请号：US15245985
申请日：2016-08-24
Applicant: General Electric Company
Inventor： John David Ward , Kelvin Rono Aaron , James Ryan Connor , Melbourne James Myers , Brad Wilson VanTassel
IPC: F01D5/22
CPC classification number: F01D5/225 , F01D5/005 , F05D2220/32 , F05D2230/10 , F05D2230/50 , F05D2230/80 , F05D2260/94 , F05D2270/332 , Y10T29/49234 , Y10T83/04
Abstract: A method is provided for modifying an airfoil shroud located at a tip of a blade of an 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 including a portion of a seal rail extending circumferentially from a radially outer surface of the airfoil shroud, and a fillet extending from the radially outer surface and positioned directly adjacent to the seal rail. The method further includes forming a relief cut in the seal rail and fillet without performing a weld process on the airfoil shroud to remove the reference location, and installing the airfoil shroud in a turbomachine directly following forming the relief cut, wherein modifying the airfoil shroud is complete following forming the relief cut.
Abstract translation: 提供了一种用于改变位于翼型件的叶片的尖端处的翼型护罩的方法，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，参考位置包括从翼型护罩的径向外表面周向延伸的密封轨道的一部分，以及从径向外表面延伸的圆角， 直接靠近密封轨。 该方法还包括在密封导轨和圆角上形成浮雕切口，而不对翼型护罩进行焊接处理以去除参考位置，并且在形成浮雕切割之后将翼型件护罩直接安装在涡轮机中，其中修改翼型护罩是 完成以后形成救济切割。
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公开(公告)号：US20140341743A1
公开(公告)日：2014-11-20
申请号：US13894514
申请日：2013-05-15
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/14
CPC classification number: F01D5/14 , F01D5/005 , F05D2230/10 , F05D2230/30 , Y10T29/49336
Abstract: Methods for modifying a turbine buckets include removing at least an original outer edge for an entire length of the slash face of the turbine bucket and adding a new material to the slash face to build a new outer edge, wherein the new outer edge extends the entire length of the slash face.
Abstract translation: 用于修改涡轮机叶片的方法包括在涡轮机叶片的斜面的整个长度上移除至少一个原始外边缘，并将新材料添加到斜面以构建新的外边缘，其中新的外边缘延伸整个 长度的斜面。
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公开(公告)号：US10174617B2
公开(公告)日：2019-01-08
申请号：US14964616
申请日：2015-12-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lawrence James Whims , James Ryan Connor , Daniel James Dorriety , Andrea Booher Kretschmar , Paul A. Cook , Brian Leslie Henderson
IPC: F01D5/00 , B33Y10/00 , B33Y80/00 , B23K1/00 , B23P6/00 , F01D5/14 , B23K35/30 , B23K35/02 , F01D5/20 , B23K1/19 , B23K1/20 , B23K101/00
Abstract: The present application provides a method of repairing a turbine blade. The method may include the steps of removing an existing tip cap from the turbine blade in whole or in part, machining the turbine blade to form a machined groove, positioning an insert in the machined groove, welding the insert to the turbine blade, and brazing the turbine blade.
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Patent Agency Ranking
公开(公告)号：US09574447B2
公开(公告)日：2017-02-21
申请号：US14023568
申请日：2013-09-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Christopher Edward Thompson , John David Ward , James Ryan Connor , Mark Lawrence Hunt , Blake Allen Fulton
CPC classification number: F01D5/14 , B23P6/005 , F01D5/005 , Y10T29/49734
Abstract: A modification process and modified article are disclosed. The modification process includes locating an area in an article, removing the area by machining to form a machined region, inserting a modification material into the machined region, securing the modification material to the article, machining the modification material flush with a geometry of the article, and applying a coating over at least a portion of the article. Another modification process includes locating an area under a suction side leading edge tip shroud fillet of an airfoil, removing the area by machining to form a hole, inserting a modification material having improved material properties as compared to an original base material into the hole, securing the modification material in place, machining the modification material and the airfoil to form a new fillet contour, and applying a coating over at least a portion of the airfoil. Also disclosed is the modified article.
Abstract translation: 公开了修改过程和修改的文章。 修改过程包括将制品中的区域定位，通过机加工去除区域以形成机加工区域，将改性材料插入加工区域，将改性材料固定到制品上，用制品的几何形状加工改性材料 ，并且在所述制品的至少一部分上涂覆涂层。 另一种改进方法包括将机翼的吸力侧前缘尖端护罩圆角下方的区域定位，通过加工去除该区域以形成孔，将与原始基底材料相比具有改善的材料特性的改性材料插入到孔中，固定 所述改性材料就位，加工所述改性材料和所述翼型件以形成新的圆角轮廓，以及在所述翼型的至少一部分上施加涂层。 还公开了修改的文章。
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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：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
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。
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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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