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1. 发明授权

US09261047B2 Jet exhaust noise reduction 有权
标题翻译：喷气排气噪音降低
公开(公告)号：US09261047B2
公开(公告)日：2016-02-16
申请号：US13482131
申请日：2012-05-29
申请人： Neal D. Domel , Daniel N. Miller
发明人： Neal D. Domel , Daniel N. Miller
IPC分类号： F02K1/34 , F02K1/38
CPC分类号： F02K1/34 , F02K1/383
摘要： Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.
摘要翻译：通过在喷气式排气流管中减弱马赫锥来减少喷气噪音。通过改变废气流管的纵向轴向芯中的废气流来减弱马赫锥。

2. 发明授权

US08960609B2 Minimally intrusive wingtip vortex wake mitigation using inside-mold-line surface modifications 有权
标题翻译：使用内模线表面修饰的微小侵入式翼尖涡流苏醒
公开(公告)号：US08960609B2
公开(公告)日：2015-02-24
申请号：US13326592
申请日：2011-12-15
申请人： Perry Wooden , Ruble E. Moor , Eric F. Charlton , Daniel N. Miller , Edwin L. Blosch , Jeffrey J. Azevedo
发明人： Perry Wooden , Ruble E. Moor , Eric F. Charlton , Daniel N. Miller , Edwin L. Blosch , Jeffrey J. Azevedo
IPC分类号： B64C23/06
CPC分类号： B64C21/02 , B64C23/065 , B64C2003/143 , B64C2230/20 , Y02T50/164 , Y02T50/166
摘要： An airfoil tip vortex mitigation device comprising an intake port disposed in a first surface of an airfoil and an exit port in fluid communication with the intake port and disposed in a second surface of the airfoil where air pressure is less than at the first surface when the airfoil is producing lift. The channel and exit port are positioned and configured to direct diverted air in such a way as to weaken an airfoil tip vortex that's produced by the airfoil when the airfoil is producing lift.
摘要翻译：一种翼型端涡流缓解装置，包括设置在翼型件的第一表面中的进气口和与进气口流体连通的出口，并且设置在翼型件的第二表面中，其中当空气压力小于第一表面时，机翼正在生产电梯。通道和出口定位和构造成引导转向的空气，以便当翼型件产生升力时削弱由翼型件产生的翼型顶端涡流。

3. 发明申请

US20130318944A1 Jet Exhaust Noise Reduction 有权
标题翻译：喷气排气降噪
公开(公告)号：US20130318944A1
公开(公告)日：2013-12-05
申请号：US13482131
申请日：2012-05-29
申请人： Neal D. Domel , Daniel N. Miller
发明人： Neal D. Domel , Daniel N. Miller
IPC分类号： F02K1/78 , F02K1/00
CPC分类号： F02K1/34 , F02K1/383
摘要： Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.
摘要翻译：通过在喷气式排气流管中减弱马赫锥来减少喷气噪音。通过改变废气流管的纵向轴向芯中的废气流来减弱马赫锥。

4. 发明申请

US20130153711A1 Minimally intrusive wingtip vortex wake mitigation using inside-mold-line surface modifications 有权
公开(公告)号：US20130153711A1
公开(公告)日：2013-06-20
申请号：US13326592
申请日：2011-12-15
申请人： Perry Wooden , Ruble E. Moor , Eric F. Charlton , Daniel N. Miller , Edwin L. Blosch , Jeffrey J. Azevedo
发明人： Perry Wooden , Ruble E. Moor , Eric F. Charlton , Daniel N. Miller , Edwin L. Blosch , Jeffrey J. Azevedo
IPC分类号： B64C23/06
CPC分类号： B64C21/02 , B64C23/065 , B64C2003/143 , B64C2230/20 , Y02T50/164 , Y02T50/166
摘要： An airfoil tip vortex mitigation device comprising an intake port disposed in a first surface of an airfoil and an exit port in fluid communication with the intake port and disposed in a second surface of the airfoil where air pressure is less than at the first surface when the airfoil is producing lift. The channel and exit port are positioned and configured to direct diverted air in such a way as to weaken an airfoil tip vortex that's produced by the airfoil when the airfoil is producing lift.

5. 发明授权

US08402738B2 Flow control redistribution to mitigate high cycle fatigue 有权
标题翻译：流量控制重新分配以减轻高周期疲劳
公开(公告)号：US08402738B2
公开(公告)日：2013-03-26
申请号：US12497225
申请日：2009-07-02
申请人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
发明人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
IPC分类号： B63H11/00
CPC分类号： F02C7/04 , F05D2270/18 , Y10S415/914 , Y10T137/0536 , Y10T137/0645
摘要： A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow. The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.
摘要翻译：公开了可操作以改善发动机入口内的压力恢复和/或变形的方法。第一流体流被提供给初级喷射涡流发生器，其可操作以将流体以第一注入速率注入到入口内的主流体流的边界层中。第二流体流以第二喷射速率被二次喷射涡流发生器注入到主流体流的边界层中。以第一注射速率和第二注射速率注入的流体可操作以在边界层内引发二次流动结构。然后，这些二次闭合结构可操作以改善或操纵入口的压力恢复。在特定发动机条件下，该方法可以重新分配第一喷射速率和第二喷射速率的比率，以便在特定的发动机条件下改善进气口的压力恢复和/或变形。

6. 发明申请

US20120222768A1 System for Global Flow Field Management Using Distributed, Surface-Embedded, Nano-Scale Boundary Layer Actuation 有权
标题翻译：使用分布式，表面嵌入式，纳米级边界层启动的全局流场管理系统
公开(公告)号：US20120222768A1
公开(公告)日：2012-09-06
申请号：US13468768
申请日：2012-05-10
申请人： Daniel N. Miller , Brent N. McCallum , Stewart A. Jenkins , David M. Wells
发明人： Daniel N. Miller , Brent N. McCallum , Stewart A. Jenkins , David M. Wells
IPC分类号： F15D1/02
CPC分类号： B64C23/06 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64C2230/18 , Y02T50/162 , Y02T50/166
摘要： Systems to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of nano-scale effectors connected to the outer surface of the aerodynamic structure to be in fluid contact with a flowing fluid when operationally flowing, to induce controlled, globally distributed disturbances at a viscous wall sublayer of a turbulent boundary layer of the flowing fluid when operationally flowing and to manipulate fluid behavior of the flowing fluid to thereby substantially reduce pressure loss associated with incipient separation of the fluid flow from portions of the aerodynamic structure.
摘要翻译：提供了用于提供分布式流量控制致动以管理全局流场的行为的系统。系统的实例可以包括具有外表面的空气动力学结构和连接到空气动力结构的外表面的多个纳米级效应器的阵列，以便在可操作地流动时与流动的流体流体接触以诱导在流动的流体的湍流边界层的粘性壁子层处的受控的全局分布的扰动，并且操纵流动流体的流体行为，从而基本上减少与流体流动与空气动力学部分的初始分离相关联的压力损失结构体。

7. 发明授权

US08242404B2 Systems and methods for plasma jets 有权
标题翻译：等离子体射流的系统和方法
公开(公告)号：US08242404B2
公开(公告)日：2012-08-14
申请号：US12968695
申请日：2010-12-15
申请人： Daniel N. Miller , Paul D. McClure , Charles J. Chase , Robert R. Boyd
发明人： Daniel N. Miller , Paul D. McClure , Charles J. Chase , Robert R. Boyd
IPC分类号： B23K10/00
CPC分类号： B64C23/005 , B64C27/18 , B64C2230/12 , F03H1/0062 , F03H1/0087 , F05D2270/172 , F15D1/12 , H05H1/54 , Y02T50/166
摘要： A plasma jet system includes a housing with a single opening. A plasma generator is coupled to ionize a fluid in the housing. An electromagnetic accelerator is coupled to generate an electric field that accelerates ionized fluid in the housing toward the opening. A controller can modulate the frequency of the electric field to cause the ionized fluid to form a plasma vortex flow through the opening. A magnetic field is applied normal to the direction of the plasma vortex flow to mitigate the momentum of the electrons. The electrons slowed by the magnetic field can be collected and conducted to a location where they are re-inserted into the plasma vortex flow to maintain charge neutrality.
摘要翻译：等离子体喷射系统包括具有单个开口的壳体。等离子体发生器耦合以离子化壳体中的流体。耦合电磁加速器以产生加速壳体中的离子化流体朝向开口的电场。控制器可以调制电场的频率，使离子化流体形成通过开口的等离子体涡流。垂直于等离子体涡流的方向施加磁场以减轻电子的动量。可以收集由磁场减慢的电子并将其传导到它们被重新插入到等离子体涡流中的位置，以维持电荷中性。

8. 发明授权

US08240616B2 Method and system for global flow field management using distributed, surface-embedded, nano-scale boundary layer actuation 有权
标题翻译：使用分布式，表面嵌入式，纳米级边界层致动的全局流场管理方法和系统
公开(公告)号：US08240616B2
公开(公告)日：2012-08-14
申请号：US12428135
申请日：2009-04-22
申请人： Daniel N. Miller , Brent N. McCallum , Stewart A. Jenkins , David M. Wells
发明人： Daniel N. Miller , Brent N. McCallum , Stewart A. Jenkins , David M. Wells
IPC分类号： B64C21/00
CPC分类号： B64C23/06 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64C2230/18 , Y02T50/162 , Y02T50/166
摘要： Systems and methods to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of effectors connected to the outer surface of the aerodynamic structure to be in fluid contact with a flowing fluid when operationally flowing, to induce controlled, globally distributed disturbances at a viscous wall sublayer of a turbulent boundary layer of the flowing fluid when operationally flowing and to manipulate fluid behavior of the flowing fluid to thereby substantially reduce pressure loss associated with incipient separation of the fluid flow from portions of the aerodynamic structure.
摘要翻译：提供了用于提供分布式流量控制致动以管理全局流场的行为的系统和方法。系统的实例可以包括具有外表面的空气动力学结构和连接到空气动力结构的外表面的多个效应器的阵列，以便在可操作地流动时与流动的流体流体接触，以诱导受控的全局在流动流体的紊流边界层的粘性壁子层处的分布干扰，并且操纵流动流体的流体行为，从而基本上减少与流体流与气动结构的部分的初始分离相关联的压力损失。

9. 发明申请

US20100084514A1 System and method to control flowfield vortices with micro-jet arrays 有权
标题翻译：用微喷射阵列控制流场涡旋的系统和方法
公开(公告)号：US20100084514A1
公开(公告)日：2010-04-08
申请号：US12319585
申请日：2009-01-09
申请人： Daniel N. Miller , Philip P. Truax , Patrick J. Yagle
发明人： Daniel N. Miller , Philip P. Truax , Patrick J. Yagle
IPC分类号： B64C21/04 , B64C19/00
CPC分类号： B64C21/02 , B64C2230/18 , Y02T50/166
摘要： The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic flow field vortices within a fluid flow over a surface using micro-jet arrays. The system and method for actively manipulating and controlling the inception point, size and trajectory of flow field vortices within the fluid flow places micro-jet arrays on surfaces bounding the fluid flow. These micro-jet arrays are then actively manipulated to control the flow behavior of the ducted fluid flow, influence the inception point and trajectory of flow field vortices within the fluid flow, and reduce flow separation within the primary fluid flow.
摘要翻译：本发明提供一种用于使用微喷射阵列主动地操纵和控制在表面上的流体流动内的空气动力学或流体动力学流场涡旋的系统和方法。用于主动操纵和控制流体流动内的流场旋涡的起始点，大小和轨迹的系统和方法将微喷射阵列放置在界定流体流动的表面上。然后主动操纵这些微喷射阵列以控制管道流体流动的流动行为，影响流体流动内的流场涡流的起始点和轨迹，并减少初级流体流中的流动分离。

10. 发明授权

US09896192B2 Minimally intrusive wingtip vortex wake mitigation using microvane arrays 有权
公开(公告)号：US09896192B2
公开(公告)日：2018-02-20
申请号：US13324537
申请日：2011-12-13
申请人： Neal D. Domel , Eric F. Charlton , Daniel N. Miller
发明人： Neal D. Domel , Eric F. Charlton , Daniel N. Miller
IPC分类号： B64C23/06 , B64C21/10
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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