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公开(公告)号：US20110095135A1
公开(公告)日：2011-04-28
申请号：US12606811
申请日：2009-10-27
申请人： Daniel N. Miller , Dan J. Baruzzini
发明人： Daniel N. Miller , Dan J. Baruzzini
IPC分类号： B64C21/10
CPC分类号： B64C23/06 , Y02T50/162
摘要： A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generators are provided, each of which is configured to generate a vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each prismatic vortex generator has a prismatic shape with a base, leading and trailing ends, and sidewalls that incline toward and join each other to form an apex. The leading end of each prismatic vortex generators is inclined away from the direction of flow.
摘要翻译： 一种用于衰减流体分离的棱柱形涡流发生器，其在超音速流动的空气结构如飞机机翼，其机身，形成喷气发动机入口的一部分的表面或经受超音速气流的类似表面之间发生。 提供了一系列棱柱形涡流发生器，其中的每一个被配置成产生一个涡流，其减弱由超音速气流引起的流动分离和重量阻力。 每个棱柱形涡流发生器具有棱柱形状，其具有基部，前端和后端以及侧壁，其倾斜并彼此连接以形成顶点。 每个棱柱形涡流发生器的前端倾斜远离流动方向。
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公开(公告)号：US20130133857A1
公开(公告)日：2013-05-30
申请号：US13307741
申请日：2011-11-30
IPC分类号： F28F7/00
CPC分类号： F01D25/305 , F02K1/40 , F02K1/822 , Y02T50/672 , Y02T50/675
摘要： An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.
摘要翻译： 一种排气冲击冷却装置，用于减少冲击表面上的排气羽流的加热效应。 排气喷嘴出口屏幕穿过排气羽流流动路径定位，并且包括多个流路发散孔，其使从排气羽流源沿着排气羽流流动路径发射的排气羽流的至少一部分展开。 流量控制射流在各自的位置排列在排气羽流流动路径中，在这些位置中，它们的操作将增加排气羽流通过筛网的流动，由此增加排气羽流与较冷的环境空气的动量和混合。
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公开(公告)号：US08210482B2
公开(公告)日：2012-07-03
申请号：US12606811
申请日：2009-10-27
申请人： Daniel N. Miller , Dan J. Baruzzini
发明人： Daniel N. Miller , Dan J. Baruzzini
IPC分类号： B64C9/00
CPC分类号： B64C23/06 , Y02T50/162
摘要： A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generators are provided, each of which is configured to generate a vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each prismatic vortex generator has a prismatic shape with a base, leading and trailing ends, and sidewalls that incline toward and join each other to form an apex. The leading end of each prismatic vortex generators is inclined away from the direction of flow.
摘要翻译： 一种用于衰减流体分离的棱柱形涡流发生器，其在超音速流动的空气结构如飞机机翼，其机身，形成喷气发动机入口的一部分的表面或经受超音速气流的类似表面之间发生。 提供了一系列棱柱形涡流发生器，其中的每一个被配置成产生一个涡流，其减弱由超音速气流引起的流动分离和重量阻力。 每个棱柱形涡流发生器具有棱柱形状，其具有基部，前端和后端以及侧壁，其倾斜并彼此连接以形成顶点。 每个棱柱形涡流发生器的前端倾斜远离流动方向。
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公开(公告)号：US09995181B2
公开(公告)日：2018-06-12
申请号：US13307741
申请日：2011-11-30
CPC分类号： F01D25/305 , F02K1/40 , F02K1/822 , Y02T50/672 , Y02T50/675
摘要： An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.
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公开(公告)号：US08403271B2
公开(公告)日：2013-03-26
申请号：US12862436
申请日：2010-08-24
IPC分类号： B64C21/00
CPC分类号： B64C30/00 , B64C21/10 , B64C2230/26 , B64D33/02 , B64D2033/026 , Y02T50/166
摘要： A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.
摘要翻译： 锥形微犁或一系列锥形微犁淹没在刚刚在倾斜冲击的反射点上游的边界层中。 每个微型犁形成一对有益的涡流，其在边界层内重新分配高能量流，从而防止或延迟流动分离。 有益的涡流对围绕平行于流体流动的轴线旋转，并且一起旋转，使得它们彼此相互感应，倾向于将它们保持在表面附近并延迟涡流剥离。
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公开(公告)号：US20120049008A1
公开(公告)日：2012-03-01
申请号：US12862436
申请日：2010-08-24
CPC分类号： B64C30/00 , B64C21/10 , B64C2230/26 , B64D33/02 , B64D2033/026 , Y02T50/166
摘要： A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.
摘要翻译： 锥形微犁或一系列锥形微犁淹没在刚刚在倾斜冲击的反射点上游的边界层中。 每个微型犁形成一对有益的涡流，其在边界层内重新分配高能量流，从而防止或延迟流动分离。 有益的涡流对围绕平行于流体流动的轴线旋转，并且一起旋转，使得它们彼此相互感应，倾向于将它们保持在表面附近并延迟涡流剥离。
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