专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07975961B2 Air induction control 有权
标题翻译：空气感应控制
公开(公告)号：US07975961B2
公开(公告)日：2011-07-12
申请号：US12619028
申请日：2009-11-16
申请人： Joseph S. Silkey , Christopher D. Wilson , Richard S. Dyer
发明人： Joseph S. Silkey , Christopher D. Wilson , Richard S. Dyer
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D5/145 , F02C7/04 , F02C7/057 , F05D2270/172 , Y02T50/671 , Y02T50/673
摘要： Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction.
摘要翻译：提供飞机的空气感应控制系统和方法。特定的飞机包括机身，一对机翼和发动机。飞行器还包括限定孔径的入口以接收用于输送到发动机的空气。当空气接近入口时，入口具有大致与空气流动方向对准的纵向轴线。该飞机还包括至少一个第一介质阻挡放电发生器，其定位成在发动机接收空气之前向空气施加第一力。第一个力作用在第一个方向。飞机还包括至少一个第二电介质阻挡放电发生器，定位成在发动机接收空气之前向空气施加第二力。第二力沿不平行于第一方向的第二方向作用。

2. 发明申请

US20110178736A1 Hydrostatic Pressure Testing System and Method 有权
标题翻译：静压试验系统及方法
公开(公告)号：US20110178736A1
公开(公告)日：2011-07-21
申请号：US13008244
申请日：2011-01-18
申请人： Lubbert Westra , Michael W. Breaux , Russell Richard, JR. , Christopher D. Wilson
发明人： Lubbert Westra , Michael W. Breaux , Russell Richard, JR. , Christopher D. Wilson
IPC分类号： G06F19/00 , G01L7/00
CPC分类号： G01M3/2815 , F17D5/02
摘要： A hydrostatic pressure testing system for hydrostatic pressure testing of pipe or other vessels. A control center may include a computer program that monitors, records, and controls the system during testing. A test fluid assembly may include a fill conduit capable of providing a test fluid to an inlet section of a vessel to be tested in response to a command from the computer program. A pressure-release safety assembly may have a vent conduit in fluid communication between an outlet section of the vessel and a safety valve. The safety valve may be in fluid communication with a bleed tank for storing an outlet flow of test fluid from the vessel. The safety valve is actuated to relieve fluid pressure in the vessel in response to a selective condition. A method of using the system to conduct hydrostatic pressure testing is also described.
摘要翻译：一种用于管道或其他船舶的静水压力试验的静水压力试验系统。控制中心可以包括在测试期间监视，记录和控制系统的计算机程序。测试流体组件可以包括能够响应于来自计算机程序的命令将测试流体提供给要测试的容器的入口部分的填充导管。压力释放安全组件可以具有在容器的出口部分和安全阀之间流体连通的排放管道。安全阀可以与泄放罐流体连通，用于存储来自容器的测试流体的出口流。致动安全阀以响应于选择性状况来释放容器中的流体压力。还描述了使用该系统进行静水压力测试的方法。

3. 发明授权

US07637455B2 Inlet distortion and recovery control system 有权
标题翻译：入口失真和恢复控制系统
公开(公告)号：US07637455B2
公开(公告)日：2009-12-29
申请号：US11403252
申请日：2006-04-12
申请人： Joseph S. Silkey , Christopher D. Wilson , Richard S. Dyer
发明人： Joseph S. Silkey , Christopher D. Wilson , Richard S. Dyer
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D5/145 , F02C7/04 , F02C7/057 , F05D2270/172 , Y02T50/671 , Y02T50/673
摘要： An air induction system for an aircraft to control distortion and pressure recovery for improved aerodynamic performance. The system includes an inlet and at least one dielectric barrier discharge generator positioned upstream of the engine for imparting momentum to a low-energy boundary layer of air. A plurality of spaced dielectric barrier discharge generators may be activated in selected combinations to optimize performance at respective flight conditions. In one embodiment, one or more generators may be oriented generally transverse relative to the flow of intake air to eject the boundary layer in a lateral direction and prevent its ingestion by the engine. In another embodiment, one or more generators may be oriented along the direction of flow to accelerate the boundary layer air.
摘要翻译：一种用于飞机控制变形和压力恢复的空气感应系统，以改善空气动力性能。该系统包括位于发动机上游的入口和至少一个介质阻挡放电发生器，用于向低能量边界层的空气赋予动量。可以以选定的组合激活多个间隔的电介质阻挡放电发生器，以在各个飞行条件下优化性能。在一个实施例中，一个或多个发生器可以相对于进气的流动大致横向定向，以沿横向排出边界层并防止其被发动机摄入。在另一个实施例中，一个或多个发生器可以沿着流动方向定向以加速边界层空气。

4. 发明授权

US08731849B2 Hydrostatic pressure testing system and method 有权
标题翻译：静水压力试验系统及方法
公开(公告)号：US08731849B2
公开(公告)日：2014-05-20
申请号：US13008244
申请日：2011-01-18
申请人： Lubbert Westra , Michael W. Breaux , Russell Richard, Jr. , Christopher D. Wilson
发明人： Lubbert Westra , Michael W. Breaux , Russell Richard, Jr. , Christopher D. Wilson
IPC分类号： G06F19/00
CPC分类号： G01M3/2815 , F17D5/02
摘要： A hydrostatic pressure testing system for hydrostatic pressure testing of pipe or other vessels. A control center may include a computer program that monitors, records, and controls the system during testing. A test fluid assembly may include a fill conduit capable of providing a test fluid to an inlet section of a vessel to be tested in response to a command from the computer program. A pressure-release safety assembly may have a vent conduit in fluid communication between an outlet section of the vessel and a safety valve. The safety valve may be in fluid communication with a bleed tank for storing an outlet flow of test fluid from the vessel. The safety valve is actuated to relieve fluid pressure in the vessel in response to a selective condition. A method of using the system to conduct hydrostatic pressure testing is also described.
摘要翻译：一种用于管道或其他船舶的静水压力试验的静水压力试验系统。控制中心可以包括在测试期间监视，记录和控制系统的计算机程序。测试流体组件可以包括能够响应于来自计算机程序的命令将测试流体提供给要测试的容器的入口部分的填充导管。压力释放安全组件可以具有在容器的出口部分和安全阀之间流体连通的排放管道。安全阀可以与泄放罐流体连通，用于存储来自容器的测试流体的出口流。致动安全阀以响应于选择性状况来释放容器中的流体压力。还描述了使用该系统进行静水压力测试的方法。

5. 发明申请

US20100140418A1 Air Induction Control 有权
标题翻译：空气感应控制
公开(公告)号：US20100140418A1
公开(公告)日：2010-06-10
申请号：US12619028
申请日：2009-11-16
申请人： Joseph S. Silkey , Christopher D. Wilson , Richard S. Dyer
发明人： Joseph S. Silkey , Christopher D. Wilson , Richard S. Dyer
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D5/145 , F02C7/04 , F02C7/057 , F05D2270/172 , Y02T50/671 , Y02T50/673
摘要： Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction.
摘要翻译：提供飞机的空气感应控制系统和方法。特定的飞机包括机身，一对机翼和发动机。飞行器还包括限定孔径的入口以接收用于输送到发动机的空气。当空气接近入口时，入口具有大致与空气流动方向对准的纵向轴线。该飞机还包括至少一个第一介质阻挡放电发生器，其定位成在发动机接收空气之前向空气施加第一力。第一个力作用在第一个方向。飞机还包括至少一个第二电介质阻挡放电发生器，定位成在发动机接收空气之前向空气施加第二力。第二力沿不平行于第一方向的第二方向作用。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式