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公开(公告)号：US07686256B2
公开(公告)日：2010-03-30
申请号：US11226033
申请日：2005-09-14
申请人： Daniel N. Miller , David D. Young
发明人： Daniel N. Miller , David D. Young
CPC分类号： F15D1/12 , B64C21/04 , B64C23/00 , B64C23/04 , B64C2230/18 , Y02T50/166
摘要： The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distributed arrays of flow control devices (submerged in the boundary layer) to create disturbances in the flow field that inhibit the growth of larger vortical structures and/or to energize the aft body shear layer to keep the shear layer attached the aft body surface. These undesirable aerodynamic phenomena produce increased vehicle drag which harms vehicle range, persistence, and loiter capabilities. Additionally, the unsteady nature of the turbulent vortical structures shed in the aft body wake region may produce increased dynamic buffeting and aft body heating by entraining nozzle jet exhaust (a.k.a. jet wash) —requiring additional structural support, shielding, and vehicle weight.
摘要翻译： 本发明提供了流场控制技术，其适应后身体区域流场以消除或减轻大量分离的流场区域和相关联的不稳定涡旋流场结构的发展。 本发明的实施例使用流动控制装置（浸没在边界层中）的一个或多个分布式阵列在流场中产生阻碍较大涡旋结构生长的干扰和/或使后身体剪切层通电以保持 剪切层附着在船体后表面。 这些不期望的空气动力学现象产生增加的车辆阻力，这损害车辆范围，持久性和怠速能力。 另外，在船尾身体尾部区域中流动的湍流涡旋结构的不稳定性质可以通过夹带喷嘴喷射排气（例如喷射洗涤） - 需要额外的结构支撑，屏蔽和车辆重量来产生增加的动态缓冲和后体加热。
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2.发明申请Adhesive Panels of Microvane Arrays for Reducing Effects of Wingtip Vortices 有权用于减少Wingtip涡流影响的微阵列胶粘剂面板公开(公告)号：US20160272302A1
公开(公告)日：2016-09-22
申请号：US14569270
申请日：2014-12-12
CPC分类号： B64C23/06 , B64C21/10 , Y02T50/162
摘要： In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing.
摘要翻译： 在一个实施例中，机翼包括低压侧，与低压侧相对的高压侧，以及使用粘合剂与低压连接的减阻装置。 减阻装置包括联接到机翼的低压侧的第一侧和与第一侧相对的第二侧，第二侧包括以阵列构造布置的多个涡流发生器，涡流发生器的阵列构造可操作以 通过在翼的低压侧的端部附近产生一个或多个叶片涡流来削弱机翼产生的翼尖涡流。
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3.发明申请公开(公告)号：US20130146715A1
公开(公告)日：2013-06-13
申请号：US13324537
申请日：2011-12-13
IPC分类号： B64C23/06
CPC分类号： B64C21/10 , B64C23/069 , Y02T50/164 , Y02T50/166
摘要： An airfoil tip vortex mitigation arrangement comprising one or more flow directors configured and positioned to re-direct freestream air over a low pressure surface of an airfoil in such a way as to displace and weaken a main tip vortex generated at a tip of the airfoil.
摘要翻译： 翼型顶端涡流减轻装置，包括一个或多个流动导向器，其构造和定位成在翼型的低压表面上重新引导自由流空气，以便移位和减弱在翼型的尖端处产生的主尖端涡流。
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公开(公告)号：US08316631B2
公开(公告)日：2012-11-27
申请号：US12894415
申请日：2010-09-30
申请人： Daniel N. Miller , Neal D. Domel , Cole W. Schemm
发明人： Daniel N. Miller , Neal D. Domel , Cole W. Schemm
IPC分类号： B64G1/40
摘要： An apparatus for reducing heating effects of an exhaust plume of a jet engine on an impinged surface includes fluid injectors disposed adjacent and aimed into an exhaust plume zone that's to be occupied by an exhaust plume when the engine is running. A flow generator transmits fluid flow into such an exhaust plume through the injectors. Each injector emits fluid in at least two divergent directions to increase the cross-sectional area of the exhaust plume by forming fluidic lobes in the exhaust plume.
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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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6.发明申请SYSTEM, METHOD, AND APPARATUS FOR CONTROL INPUT PREDICTION AND STATE VERIFICATION OF FLUIDIC VECTORING EXHAUST IN HIGH PERFORMANCE AIRCRAFT 有权用于控制输入预测的系统，方法和装置以及高性能飞机中的流体检测排气的状态验证公开(公告)号：US20080149742A1
公开(公告)日：2008-06-26
申请号：US11615050
申请日：2006-12-22
申请人： Rob S. Burgun , Kerry B. Ginn , Daniel N. Miller
发明人： Rob S. Burgun , Kerry B. Ginn , Daniel N. Miller
IPC分类号： F02K1/15
CPC分类号： F02K1/15 , B64C15/02 , F02K1/008 , F02K1/28 , F05D2270/051 , F05D2270/301
摘要： A non-invasive system, method, and apparatus for control input prediction and state verification of an aircraft's fluidic vectoring exhaust is disclosed. The control system derives a desired vector state, then predicts and sets the fluidic injection input required to produce the desired vector state. A vectored state verification routine is used to determine the resulting vector state for feedback to the control system.
摘要翻译： 公开了一种用于控制输入预测和飞机的流体矢量化排气的状态验证的非侵入性系统，方法和装置。 控制系统导出所需的矢量状态，然后预测并设定产生所需矢量状态所需的流体注入输入。 矢量状态验证程序用于确定所得矢量状态以反馈给控制系统。
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公开(公告)号：US06308740B1
公开(公告)日：2001-10-30
申请号：US09639187
申请日：2000-08-15
IPC分类号： E03B500
CPC分类号： F02C9/50 , F02C7/04 , F04B45/04 , F04F5/16 , F04F5/54 , Y10T137/87619 , Y10T137/87652
摘要： The present invention reveals a method and apparatus for more efficiently injecting a primary fluid flow in a fluid ejector used to pump lower velocity fluid from a secondary source. In one embodiment, the primary fluid flow is a pulsed or unsteady fluid flow contained within an inner nozzle situated within a secondary flow field. This secondary fluid flow is bounded within the walls of an ejector or shroud. The secondary and primary fluid flows meet within the ejector shroud section wherein the secondary fluid flow is entrained by the primary fluid flow. The geometry of the ejector shroud section where the primary and secondary fluids mix is such as to allow the beginning of primary injector pulse to be synchronized with an acoustic wave moving upstream through the ejector initiated by the exiting of the previous pulse from the ejector shroud. The ejector's geometric properties are determined by the acoustic properties, frequency, duty cycle, and amplitude, of the pulsed primary fluid flow. Furthermore, the frequency, duty cycle and amplitude of the primary fluid flow may be varied in order to vary the efficiency of the injector.
摘要翻译： 本发明揭示了一种用于在用于从次级源泵送较低速度流体的流体喷射器中更有效地喷射主流体流的方法和装置。 在一个实施例中，主流体流是包含在位于二次流场内的内部喷嘴内的脉冲或不稳定流体流。 该次级流体流动在喷射器或护罩的壁内。 次级和初级流体流动在喷射器护罩部分内相交，其中次流体流被主流体流动夹带。 初级和次级流体混合的喷射器护罩部分的几何形状允许初级喷射器脉冲的开始与通过喷射器的上游移动的声波同步，该喷射器由从喷射器护罩的先前脉冲的离开开始。 喷射器的几何特性由脉冲初级流体流的声学特性，频率，占空比和幅度决定。 此外，可以改变初级流体流的频率，占空比和幅度，以改变喷射器的效率。
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公开(公告)号：US09896192B2
公开(公告)日：2018-02-20
申请号：US13324537
申请日：2011-12-13
CPC分类号： B64C21/10 , B64C23/069 , Y02T50/164 , Y02T50/166
摘要： An airfoil tip vortex mitigation arrangement comprising one or more flow directors configured and positioned to re-direct freestream air over a low pressure surface of an airfoil in such a way as to displace and weaken a main tip vortex generated at a tip of the airfoil.
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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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10.发明授权公开(公告)号：US08408281B2
公开(公告)日：2013-04-02
申请号：US11872165
申请日：2007-10-15
CPC分类号： B64D13/00 , B64D2013/0674 , Y02T50/44 , Y02T50/56
摘要： A pulsed-jet active flowfield control actuation system enhances the rate of heat transfer and heat removal in a heat exchanger for better management of thermal loads. The pulsed jet actuators impart an unsteady component of velocity to the working fluid of the heat exchanger. This design increases the convective heat transfer, and avoids increases in heat exchanger volume and weight for a given performance value.
摘要翻译： 脉冲喷射主动流场控制致动系统提高热交换器中的传热速率和散热速率，从而更好地管理热负荷。 脉冲喷射致动器对热交换器的工作流体施加不稳定的速度分量。 这种设计增加了对流传热，并避免了给定性能值的热交换器体积和重量的增加。
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