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11.
公开(公告)号:US20170120359A1
公开(公告)日:2017-05-04
申请号:US15196165
申请日:2016-06-29
IPC分类号: B23H3/04 , B23K26/342 , B22F3/105 , B23H9/10
CPC分类号: B23H3/04 , B22F3/1055 , B22F3/24 , B22F5/009 , B22F5/04 , B22F5/10 , B22F2998/10 , B23H3/06 , B23H9/001 , B23H9/02 , B23H9/10 , B23K26/342 , B23K2101/001 , B23K2103/05 , B23K2103/14 , B23K2103/26 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B33Y80/00 , B33Y99/00 , C25F3/16 , Y02P10/295 , B22F2003/247 , B22F2003/241
摘要: A system is configured for machining a workpiece of a lattice structure, the system includes an electrode of a lattice structure, an electrolyte supply, and a power supply. The workpiece and the electrode are intertwined with each other and electrically isolated from each other. The electrolyte supply is configured for circulating an electrolyte around and between the workpiece and the electrode. The power supply is configured for applying a voltage between the workpiece and the electrode to facilitate smoothing surfaces of the workpiece.
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公开(公告)号:US20170036284A1
公开(公告)日:2017-02-09
申请号:US15299005
申请日:2016-10-20
申请人: MTU Aero Engines AG
CPC分类号: B23H9/10 , B23H3/00 , C25F3/00 , F01D5/02 , F01D5/143 , F01D5/225 , F01D25/28 , F05B2230/101 , F05D2220/323 , F05D2230/10 , F05D2230/11 , Y02T50/673
摘要: A method for machining a workpiece is provided. An electrode is moved linearly in the direction of the workpiece to cause material to be removed from the workpiece, at least one end of a surface of the workpiece running obliquely to a guide edge of the electrode machining this surface. The electrode is moved at least partially with the electrode surface parallel to the surface, so that during the approach to the workpiece, areas of the workpiece having an irregular edge machined at a different intensity are formed, the difference in intensity of machining on the edge of the surface to be machined being compensated in that the surface to be machined is provided with a height profile adapted to the shape of the end of the surface to be machined. A blade ring segment and blade ring is also disclosed.
摘要翻译: 提供了一种加工工件的方法。 电极沿着工件的方向线性移动以使材料从工件移除,工件的表面的至少一端倾斜于电极的引导边缘加工该表面。 电极至少部分地与电极表面平行移动至表面,这样在接近工件时,形成加工成不同强度的不规则边缘的工件区域,边缘上的加工强度差异 要被加工的表面被补偿为:被加工表面设置有适于被加工表面的端部形状的高度分布。 还公开了一种叶片环段和叶片环。
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公开(公告)号:US09561555B2
公开(公告)日:2017-02-07
申请号:US13729286
申请日:2012-12-28
发明人: James M. Koonankeil , Edward F. Pietraszkiewicz , Karl A. Schachtner , Kevin J. Klinefelter , Markus W. Fritch , Jason Daley
CPC分类号: B23H1/00 , B23H7/265 , B23H7/30 , B23H9/10 , F01D5/187 , F05D2230/12 , F05D2240/12 , F05D2240/81 , Y02T50/676 , Y10T29/49323 , Y10T29/49341
摘要: A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening.
摘要翻译: 在部件中加工冷却孔的方法包括以下步骤:将容纳电极的放电加工引导件插入部件的内部空腔中,并用电极将冷却孔加工到部件的壁中。 燃气涡轮发动机部件包括提供内腔的第一和第二隔开的壁。 第一个墙壁有外表面和内表面。 内表面面向内腔。 冷却孔从内表面到外表面延伸穿过第一壁。 冷却孔包括分别设置在内表面和外表面上的入口和出口。 出口开口包括比入口开口的横截面面积小的横截面面积。
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公开(公告)号:US20160375527A1
公开(公告)日:2016-12-29
申请号:US14211643
申请日:2014-03-14
CPC分类号: B23P6/002 , B23H9/10 , B23K26/34 , B23K2101/001 , B23P6/007 , B24B19/14 , F01D5/005 , F01D5/18 , F01D5/20 , F05D2220/32 , F05D2230/12 , F05D2230/234 , F05D2230/30 , F05D2230/80 , F05D2240/307 , Y10T29/49318
摘要: A method for repairing a blade tip of a turbine blade based on welding below and above a designated depth recommended for repair of turbine blades. A damaged portion of the turbine blade is inspected to identify a standard cut portion and an angled cut portion. The standard cut portion is damaged above a standard cut line and the angled cut portion is damaged below the standard cut line. The damaged portion of the turbine blade is removed. The standard cut portion is removed using a first removal process and the angled cut portion is removed using a second removal process. The angled cut portion is built up with a first weld repair process. The angled cut portion is built up to the standard cut portion. The standard cut portion and the angled cut portion are built up with a second weld repair process.
摘要翻译: 一种基于推荐用于修复涡轮叶片的指定深度的下方的焊接修复涡轮叶片的叶片尖端的方法。 检查涡轮机叶片的损坏部分以识别标准切割部分和倾斜切割部分。 标准切割部分在标准切割线以上损坏,角形切割部分损坏到标准切割线以下。 涡轮叶片的损坏部分被去除。 使用第一去除工艺去除标准切割部分,并且使用第二去除工艺去除成角度的切割部分。 倾斜切割部分由第一焊接修复过程构成。 倾斜切割部分被建立到标准切割部分。 标准切割部分和倾斜切割部分由第二焊接修复过程构成。
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公开(公告)号:US20160243620A1
公开(公告)日:2016-08-25
申请号:US15032752
申请日:2014-12-03
发明人: Evan Butcher
CPC分类号: B22F3/1055 , B22F2003/1058 , B23H9/10 , B23K15/0086 , B23K26/34 , B23K26/342 , B23K2101/001 , B23P15/006 , B23P15/02 , B33Y10/00 , B33Y80/00 , F01D5/02 , F01D5/12 , F01D5/141 , F04D29/181 , F04D29/2238 , F04D29/28 , F04D29/32 , F04D29/321 , F05D2230/22 , F05D2230/31 , Y02P10/295
摘要: A method includes forming a component on a layer-by-layer basis using additive manufacturing, forming a shroud support structure on a layer-by-layer basis using additive manufacturing, and removing the shroud support structure after forming the component. The component includes a central portion and at least one feature extending generally radially from a first end connected to the central portion to a second end distal to the central portion. The shroud support structure is connected to the second end of the at least one feature.
摘要翻译: 一种方法包括使用添加剂制造在逐层的基础上形成部件,使用添加剂制造在层叠的基础上形成护罩支撑结构,以及在形成部件之后去除护罩支撑结构。 该部件包括中心部分和至少一个特征,该特征从连接到中心部分的第一端部至远离中心部分的第二端大致径向延伸。 护罩支撑结构连接到至少一个特征的第二端。
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公开(公告)号:US09416462B2
公开(公告)日:2016-08-16
申请号:US13823520
申请日:2011-09-13
申请人: Yimin Zhan , Yuanyuan Guo , Yuanfeng Luo , Renewi Yuan , Zhixue Peng , Garth M. Nelson , Massimo Arcioni , Francescosaverio Chiari , Hongtao Li
发明人: Yimin Zhan , Yuanyuan Guo , Yuanfeng Luo , Renewi Yuan , Zhixue Peng , Garth M. Nelson , Massimo Arcioni , Francescosaverio Chiari , Hongtao Li
摘要: A machining system for machining a workpiece is provided. The machining system comprises a machine tool, a plurality of cutting tools, a CNC controller. The plurality of cutting tools comprises an electrode and a conventional cutting tool exchangeably disposed on the machine tool. The machining system further comprises a power supply, a process controller, and an electrolyte supply, wherein the machine tool, the electrode, the CNC controller, the power supply, the process controller and the electrolyte supply are configured to cooperate to function as an electroerosion machining device, wherein the machine tool, the CNC controller, the conventional cutting tool and the electrolyte supply are configured to cooperate to function as a conventional machining device, and wherein the machining system is configured to function alternately as the electroerosion machining device and the conventional machining device.
摘要翻译: 提供了一种用于加工工件的加工系统。 该加工系统包括机床,多个切削工具,CNC控制器。 多个切割工具包括电极和可交换地设置在机床上的常规切割工具。 该加工系统还包括电源,过程控制器和电解质供应源,其中机床,电极,CNC控制器,电源,过程控制器和电解质供应被配置成配合起电极作用 其特征在于,上述机床,上述CNC控制器,上述常规切削工具和上述电解液供给构成为能够起到传统加工装置的作用,其特征在于,上述加工系统被配置为交替地作为电蚀加工装置, 加工装置。
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17.
公开(公告)号:US20160067836A1
公开(公告)日:2016-03-10
申请号:US14482273
申请日:2014-09-10
CPC分类号: B23P6/005 , B23H1/00 , B23H1/04 , B23H9/10 , B23P6/045 , F01D5/005 , F05D2230/12 , F05D2230/237 , F05D2240/80
摘要: A method of remanufacturing a turbine component includes electrical discharge machining a puck via the turbine component to form an electrical discharged machined puck; and brazing the electrical discharged machined puck to the turbine component.
摘要翻译: 涡轮机部件的再制造方法包括经由涡轮机部件对圆盘进行放电加工以形成放电加工的圆盘; 并将放电的机电圆盘钎焊到涡轮部件上。
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公开(公告)号:US20160053763A1
公开(公告)日:2016-02-25
申请号:US14754395
申请日:2015-06-29
发明人: Thomas Toellner
CPC分类号: F04D15/0055 , A61M1/1008 , A61M1/101 , A61M1/1024 , A61M1/1034 , A61M1/12 , A61M1/122 , A61M1/125 , A61M2207/00 , B23H9/10 , B23K26/21 , B23K26/38 , F04D3/00 , F04D3/02 , F04D29/181 , F04D29/247 , Y10T29/49337
摘要: The invention relates to a compressible and expandable blade (2) for the rotor of a fluid pump (30) having at least two lamellae (3, 4, 5) which are disposed adjacently, are pivo table respectively relative to an axis of rotation (Ia) of the rotor and moveable relative to each other, and abut against each other in the expanded state of the blade such that they form together a continuous blade surface.
摘要翻译: 本发明涉及一种用于流体泵(30)的转子的可压缩和可膨胀的叶片(2),其具有相对于旋转轴线分别相邻设置的至少两个薄片(3,4,5) 1a)并且可相对于彼此移动,并且在叶片的膨胀状态下彼此抵靠,使得它们一起形成连续的叶片表面。
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公开(公告)号:US20160052057A1
公开(公告)日:2016-02-25
申请号:US14779867
申请日:2014-03-25
发明人: JinQuan Xu
CPC分类号: B22F3/1055 , B22F5/009 , B22F5/04 , B22F5/10 , B22F2003/1056 , B22F2998/10 , B23H1/00 , B23H7/02 , B23H9/006 , B23H9/10 , B23K15/0086 , B23K26/082 , B23K26/0853 , B23K26/0876 , B23K26/342 , B23K2101/001 , B23P15/02 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B33Y80/00 , F01D5/187 , F05D2230/10 , F05D2230/22 , F05D2230/31 , F05D2240/31 , F05D2260/202 , F05D2260/2212 , Y02P10/295 , B22F2003/247
摘要: A method of fabricating a gas turbine engine component comprises building and machining a hollow workpiece. The workpiece is built via additive manufacturing to create a coarse structure that turbulates cooling flow. At least a portion of the workpiece is machined via subtractive manufacturing to create a smooth surface that promotes laminar flow.
摘要翻译: 一种制造燃气涡轮发动机部件的方法包括建造和加工中空工件。 通过添加剂制造工件,以产生使冷却流动紊乱的粗糙结构。 工件的至少一部分通过减法制造加工,以产生促进层流的光滑表面。
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公开(公告)号:US20160017716A1
公开(公告)日:2016-01-21
申请号:US14763945
申请日:2014-02-10
发明人: Anders Haggmark , Janos Szijarto
CPC分类号: F01D5/18 , B23H9/10 , F01D9/041 , F01D11/006 , F05D2220/30 , F05D2230/10 , F05D2240/12 , F05D2240/122 , F05D2240/30 , F05D2240/304 , F05D2240/80 , F05D2260/94 , F05D2260/941
摘要: A turbomachine component with a stress relief cavity includes an airfoil and a platform. The airfoil has a trailing edge. The platform has a trailing edge region, a seal strip slot and a stress relief cavity. The trailing edge region supports at least a part of the trailing edge. The stress relief cavity extends inside the platform into the trailing edge region and is an extension of the seal strip slot.
摘要翻译: 具有应力消除腔的涡轮机组件包括翼型件和平台。 机翼具有后缘。 平台具有后缘区域,密封条槽和应力消除腔。 后缘区域支持后缘的至少一部分。 应力消除腔在平台内延伸到后缘区域中,并且是密封条槽的延伸部。
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