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公开(公告)号：US20150082410A1
公开(公告)日：2015-03-19
申请号：US14339421
申请日：2014-07-23
IPC分类号： H04L29/06
CPC分类号： H04L63/08 , G06F16/178 , H04L63/0853
摘要： There is provided a method and system for securely coupling and transferring data between devices. In a preferred embodiment, the devices may comprise two devices, a transferring device and a receiving device, and both devices are mobile devices. Embodiments of the present invention allow the wireless transfer of data such as contacts, photo images, video files, or other data from one device to another device, without need for special hardware or cabling.
摘要翻译： 提供了一种用于在设备之间安全地耦合和传送数据的方法和系统。 在优选实施例中，设备可以包括两个设备，传送设备和接收设备，并且两个设备都是移动设备。 本发明的实施例允许将诸如联系人，照片图像，视频文件或其他数据的数据从一个设备无线传输到另一个设备，而不需要特殊的硬件或电缆。
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2.发明申请公开(公告)号：US20110262277A1
公开(公告)日：2011-10-27
申请号：US13140463
申请日：2008-12-18
申请人： Roger Sjöqvist , Dan Gustafsson , Hasse Lindell
发明人： Roger Sjöqvist , Dan Gustafsson , Hasse Lindell
CPC分类号： F01D9/041 , F01D25/162 , F04D27/0292 , F04D29/023 , F04D29/083 , F04D29/526 , F05D2230/232 , F05D2300/502 , F05D2300/603 , Y02T50/672 , Y10T29/4932
摘要： A gas turbine composite workpiece, such as a workpiece forming a part of a gas turbine casing, is provided. The workpiece includes at least two components joined by at least one weld seam. In order to reduce thermal stresses of the workpiece during operation, the weld seam is interrupted by at least one aperture. In order to reduce the exchange of gases between the workpiece's sides, the workpiece may be equipped with an arrangement for preventing gas flow through the aperture.
摘要翻译： 提供了一种燃气轮机复合工件，例如形成燃气轮机壳体的一部分的工件。 工件包括由至少一个焊缝连接的至少两个部件。 为了减少工件在工作时的热应力，焊缝被至少一个孔断开。 为了减少工件侧面之间的气体交换，工件可以配备有用于防止气体流过孔的装置。
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公开(公告)号：US09822652B2
公开(公告)日：2017-11-21
申请号：US14408058
申请日：2012-07-03
申请人： Roger Sjoqvist , Hakan Jakobsson , Dan Gustafsson
发明人： Roger Sjoqvist , Hakan Jakobsson , Dan Gustafsson
CPC分类号： F01D9/041 , B23K31/02 , F01D25/246 , F01D25/28 , F05D2230/232 , Y02T50/671 , Y10T29/49323
摘要： A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, wherein the supporting structure has an inlet side for primary gas flow entrance and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side, a trailing edge directed towards the outlet side, and two opposite sides connecting the leading edge and the trailing edge, and wherein at least a first of said radial elements is connected to an adjacent part of the supporting structure via a weld joint that extends across the leading edge and circumferentially at least partly around the first radial element.
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公开(公告)号：US20150176420A1
公开(公告)日：2015-06-25
申请号：US14408058
申请日：2012-07-03
申请人： Roger Sjoqvist , Hakan Jakobsson , Dan Gustafsson
发明人： Roger Sjoqvist , Hakan Jakobsson , Dan Gustafsson
CPC分类号： F01D9/041 , B23K31/02 , F01D25/246 , F01D25/28 , F05D2230/232 , Y02T50/671 , Y10T29/49323
摘要： A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, wherein the supporting structure has an inlet side for primary gas flow entrance and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side, a trailing edge directed towards the outlet side, and two opposite sides connecting the leading edge and the trailing edge, and wherein at least a first of said radial elements is connected to an adjacent part of the supporting structure via a weld joint that extends across the leading edge and circumferentially at least partly around the first radial element
摘要翻译： 用于燃气涡轮发动机的支撑结构包括内环，外环和连接内环和外环的多个周向隔开的承载径向元件，所述径向元件构造成在内环和外环之间传递载荷 其中，在所述内环和外环之间限定用于主轴向气流的气体通道，其中所述支撑结构具有用于初级气流入口的入口侧和用于初级气体流出的出口侧，其中所述径向元件具有翼型 形状，其具有朝向入口侧的前缘，指向出口侧的后缘和连接前缘和后缘的两个相对侧，并且其中至少第一个所述径向元件连接到 所述支撑结构经由焊接接头延伸穿过所述前缘并且周向至少部分地围绕所述第一径向元件
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