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1. 发明申请

US20190002035A1 AERODYNAMIC DEVICES FOR MOVING VEHICLES 审中-公开
公开(公告)号：US20190002035A1
公开(公告)日：2019-01-03
申请号：US16123165
申请日：2018-09-06
申请人： INVENTURE HOLDINGS, LLC
发明人： Timothy J. Brereton , Joseph A. Schetz
IPC分类号： B62D35/00 , F15D1/00 , B62D63/08 , B62D37/02
CPC分类号： B62D35/001 , B60K1/04 , B60K16/00 , B60K2001/0438 , B60K2016/003 , B60Y2200/142 , B60Y2200/145 , B60Y2400/216 , B62D37/02 , B62D63/08 , F15D1/008
摘要： A vehicle or trailer assembly is disclosed comprising at least one fan positioned on an exterior of the vehicle or trailer, wherein the at least one fan redirects or accelerates air moving over, around, or through the exterior of the vehicle or trailer. Also disclosed is a fan assembly comprising a manifold configured to be positioned on an outside surface of a vehicle, along an axis transverse to a direction of travel of the vehicle. The fan assembly also includes a plurality of motorized fans rotatably mounted along the axis of the manifold, such that the motorized fans are configured to accelerate air passing along the outside surface or within an exterior of the vehicle, in the direction of travel of the vehicle.

2. 发明授权

US09969497B2 Noise and drag reducing cabin pressure outflow valve 有权
公开(公告)号：US09969497B2
公开(公告)日：2018-05-15
申请号：US14502633
申请日：2014-09-30
申请人： The Boeing Company
发明人： John H. Gibbs
IPC分类号： B64D13/00 , E04B1/00 , B64D13/02 , G05D16/20 , F15D1/00
CPC分类号： B64D13/02 , F15D1/004 , F15D1/0055 , F15D1/008 , F15D1/0095 , G05D16/202
摘要： A system and method for regulating pressure inside a vehicle (“cabin pressure”) is disclosed. The system can include a forward gate and an aft gate that can be moved from a closed position to an open position to release cabin pressure in a controlled manner. The forward gate, the aft gate, or both can comprise an interior cavity and one or more permeable surfaces. When open, or partially open, an airflow can be created by a pressure differential between the cabin pressure and the pressure outside the vehicle (“atmospheric pressure”). At least a portion of the airflow can flow through the one or more permeable surfaces and the hollow cavity of the forward gate, the aft gate, or both to promote laminar flow through the gates and into the atmosphere alongside the vehicle (e.g., an aircraft fuselage). In this manner, flow efficiency can be increased and noise reduced.

3. 发明申请

US20180117607A1 SYSTEMS, METHODS, AND APPARATUSES FOR PROVIDING VISCOUS FLUID IN A PARTICULAR FORMAT AND IMPLEMENTATIONS THEREOF 审中-公开
公开(公告)号：US20180117607A1
公开(公告)日：2018-05-03
申请号：US15856587
申请日：2017-12-28
申请人： Charles Robert Safarik , Prashanth Sridharan
发明人： Charles Robert Safarik , Prashanth Sridharan
IPC分类号： B05B7/04 , B05B7/06
CPC分类号： B05B7/0483 , B05B7/0433 , B05B7/0491 , B05B7/064 , B05B7/067 , F02M1/00 , F15D1/008
摘要： The present invention involves providing a viscous fluid in a particular format and implementations thereof. In particular, a viscous slave fluid is provided in a particular format, wherein the particular format can be an end result or an intermediate result for the viscous fluid. In the case of an intermediate result, the viscous fluid in the second format may be further processed to a third format. Implementations or applications include supercharged fuel injection systems, methods, and apparatuses for internal combustion, lean-burn oil pre-mixing systems, methods, and apparatuses for liquid fuel combustion, and medical or biomedical devices, systems, and methods.

4. 发明申请

US20180073527A1 Piezoelectric Actuators Optimized for Synthetic Jet Actuators 审中-公开
公开(公告)号：US20180073527A1
公开(公告)日：2018-03-15
申请号：US15787415
申请日：2017-10-18
申请人： The Boeing Company
发明人： Edward A. Whalen , Steven F. Griffin , Marthinus Cornelius van Schoor , Conor Clery
IPC分类号： F15D1/00 , F04B43/04 , H01L41/22
CPC分类号： F15D1/008 , F04B43/046 , H01L41/22
摘要： A synthetic jet actuator and a method for optimizing a synthetic jet actuator to meet operating requirements and physical constraints may include estimating dimension and a resonance frequency of an air cavity of the synthetic jet actuator, and using the estimated resonance frequency to the estimate dimensions of a piezoelectric actuator of the synthetic jet actuator. Individual simulations of the air cavity and piezoelectric actuator, and a coupled simulation may be performed using the estimated dimensions, and the dimensions may be revised and simulations re-executed to match the resonance frequencies of the air chamber and the piezoelectric actuator. The method maybe yield a synthetic jet actuator having a resonance frequency of the piezoelectric actuator that is approximately equal to a quarter-wavelength resonance frequency of the air cavity.

5. 发明申请

US20160333904A1 Piezoelectric Actuators Optimized for Synthetic Jet Actuators 有权
标题翻译：压电致动器优化用于合成喷气致动器
公开(公告)号：US20160333904A1
公开(公告)日：2016-11-17
申请号：US14712510
申请日：2015-05-14
申请人： The Boeing Company
发明人： Edward A. Whalen , Steven F. Griffin , Marthinus Cornelius van Schoor , Conor Clery
IPC分类号： F15D1/00 , H01L41/22
CPC分类号： F15D1/008 , F04B43/046 , H01L41/22
摘要： A synthetic jet actuator and a method for optimizing a synthetic jet actuator to meet operating requirements and physical constraints may include estimating dimension and a resonance frequency of an air cavity of the synthetic jet actuator, and using the estimated resonance frequency to the estimate dimensions of a piezoelectric actuator of the synthetic jet actuator. Individual simulations of the air cavity and piezoelectric actuator, and a coupled simulation may be performed using the estimated dimensions, and the dimensions may be revised and simulations re-executed to match the resonance frequencies of the air chamber and the piezoelectric actuator. The method maybe yield a synthetic jet actuator having a resonance frequency of the piezoelectric actuator that is approximately equal to a quarter-wavelength resonance frequency of the air cavity.
摘要翻译：合成射流致动器和用于优化合成射流致动器以满足操作要求和物理约束的方法可以包括估计合成射流致动器的空气腔的尺寸和共振频率，并将所估计的共振频率用于估计的合成射流致动器的压电致动器。空气腔和压电致动器的单独模拟以及耦合模拟可以使用估计的尺寸进行，并且可以修改尺寸并重新执行模拟以匹配气室和压电致动器的谐振频率。该方法可以产生具有近似等于空气腔的四分之一波长共振频率的压电致动器的共振频率的合成射流致动器。

6. 发明申请

US20160332742A1 SYSTEMS AND METHODS FOR SELECTIVE CONTROL OF FUEL TANKS 有权
标题翻译：燃油箱选型控制系统与方法
公开(公告)号：US20160332742A1
公开(公告)日：2016-11-17
申请号：US14712635
申请日：2015-05-14
申请人： Elwha LLC
发明人： Alistair K. Chan , Jesse R. Cheatham, III , Hon Wah Chin , Roderick A. Hyde , Muriel Y. Ishikawa , Jordin T. Kare , Max N. Mankin , Nathan P. Myhrvold , Tony S. Pan , Robert C. Petroski , Clarence T. Tegreene , Nicholas W. Touran , David B. Tuckerman , Yaroslav A. Urzhumov , Lowell L. Wood, JR. , Victoria Y.H. Wood
IPC分类号： B64D37/06 , F15D1/00
CPC分类号： F15D1/008 , B60K15/077 , B60K2015/03375 , B60Y2306/01 , B64D37/00
摘要： A fuel tank includes a port and an open-cell foam. The open-cell foam is configured to retain a liquid fuel by an interfacial surface tension between the open-cell foam and the liquid fuel. The open-cell foam is configured to selectively release the liquid fuel when a surfactant is applied to the open-cell foam to reduce the interfacial surface tension between the open-cell foam and the liquid fuel.
摘要翻译：燃料箱包括端口和开孔泡沫。开孔泡沫构造成通过开孔泡沫体和液体燃料之间的界面表面张力来保持液体燃料。开孔泡沫构造成当将表面活性剂施加到开孔泡沫体上以选择性地释放液体燃料以降低开孔泡沫体和液体燃料之间的界面张力。

7. 发明申请

US20140360587A1 REDUCING FRICTION OF A VISCOUS FLUID FLOW IN A CONDUIT 有权
标题翻译：减少流体中粘度流体的摩擦
公开(公告)号：US20140360587A1
公开(公告)日：2014-12-11
申请号：US14368065
申请日：2013-02-07
申请人： COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEACH ORGANISATION
发明人： Jie Wu , Lachlan Graham , Gregory Mark Short , Dean William Harris
IPC分类号： F17D1/17
CPC分类号： F17D1/17 , F15D1/008 , F15D1/06 , F17D1/16 , Y10T137/0391 , Y10T137/2076 , Y10T137/2082
摘要： A device for reducing friction of a viscous fluid flow in a conduit includes a body (10,110) positionable to define at least a segment of a flow path for the viscous fluid in or contiguous with the conduit, a cavity (40,140) in the body for retaining lubricating fluid, and at least one port (42,142) in the body for delivering lubricating fluid to the cavity. A fluid outlet arrangement (48,148) from the cavity delivers lubricating fluid to the flow path to form a downstream lubricating film about viscous fluid flowing therein. The fluid outlet arrangement comprises a substantially continuous opening or ring of close spaced openings about the flow path. The cavity comprises an array of passages in the body that includes a plurality of elongate passages (55,155) that extend about the flow path effective collectively to reduce the pressure variation and therefore velocity variation of the delivered lubricating fluid along the outlet arrangement. A corresponding method is also disclosed.
摘要翻译：用于减少导管中的粘性流体流的摩擦的装置包括主体（10,110），其可定位成限定用于粘性流体或与导管邻接的粘性流体的流路的至少一段，所述主体中的空腔（40,140）保持润滑流体，以及至少一个端口（42,142），用于将润滑流体输送到腔体。来自空腔的流体出口装置（48,148）将润滑流体输送到流动路径，以在其中流动的粘性流体形成下游润滑膜。流体出口装置包括围绕流动路径的基本上连续的开口或环的密闭间隔的开口。空腔包括主体中的通道阵列，其包括多个细长通道（55,155），所述多个细长通道围绕流动路径延伸，共同有效地降低压力变化并因此减小输送的润滑流体沿出口装置的速度变化。还公开了相应的方法。

8. 发明授权

US08382043B1 Method and apparatus for aerodynamic flow control using compact high-frequency fluidic actuator arrays 有权
标题翻译：使用紧凑型高频流体驱动器阵列进行气动流量控制的方法和装置
公开(公告)号：US08382043B1
公开(公告)日：2013-02-26
申请号：US12804225
申请日：2010-07-16
申请人： Surya Raghu
发明人： Surya Raghu
IPC分类号： B64C21/04
CPC分类号： B64C21/04 , B64C2230/04 , B64C2230/18 , F15D1/008 , Y02T50/166
摘要： The present invention is directed to the manufacture of and the use of an aerodynamic flow control device having a compact array of a plurality of fluidic actuators in planar, curved, circular and annular configurations. The compact array of fluidic actuators of the invention may be designed to produce oscillating or pulsed jets at the exit ports with frequencies in the range of 1-22 kHz. They may be integrally manufactured along with the wing sections, flaps, tail and rudder of airplane, the inlet or exit geometries of a jet engine. When supplied with a source of fluid such as air, these arrays of actuators produce a set of fluid jets of random phase of high velocity and influence the main stream of air over the subject surface. The beneficial effects of modifying flow using the present invention include increased lift, reduced drag, improved performance and noise reduction in jet engines.
摘要翻译：本发明涉及一种具有平面，弯曲，圆形和环形构造的多个流体致动器的紧凑阵列的空气动力学流量控制装置的制造和使用。本发明的流体致动器的紧凑阵列可被设计成在出口处产生振荡或脉冲射流，频率范围为1-22kHz。它们可以与飞机的翼部，翼片，尾翼和方向舵，喷气发动机的入口或出口几何形状一体制造。当供应诸如空气的流体源时，这些致动器阵列产生一组高速度的随机相的流体射流并影响主体表面上的主要空气流。使用本发明改进流动的有益效果包括增加升力，降低阻力，提高喷气发动机的性能和降噪。

9. 发明申请

US20050199052A1 System and method for closed loop control of boundary layer shear stress 有权
标题翻译：边界层剪切应力闭环控制系统与方法
公开(公告)号：US20050199052A1
公开(公告)日：2005-09-15
申请号：US11076274
申请日：2005-03-09
申请人： Siva Mangalam
发明人： Siva Mangalam
IPC分类号： G01M9/00
CPC分类号： G01M9/06 , B64C23/005 , B64D43/02 , F15D1/0065 , F15D1/008 , Y02T50/166
摘要： A system is provided for controlling boundary layer shear stress adjacent a surface over which a fluid stream has been established. The system comprises a boundary layer control device adapted for altering at least one flow characteristic within a boundary layer in a selected region of the surface. The system further comprises a shear stress measurement system comprising a hot film sensor arrangement having at least one hot film sensor element appliable to the surface in the selected region. The at least one hot film sensor element is connected to an anemometer circuit configured to provide a sensor signal corresponding to heat transfer from the associated hot film sensor to the fluid stream. The system also comprises a control module in communication with the anemometer arrangement and the boundary layer control device. The control module is adapted for receiving and processing sensor signals signal from the anemometer circuit and for providing input signals to the boundary layer control device.
摘要翻译：提供了一种用于控制邻近流体流已经建立的表面的边界层剪切应力的系统。该系统包括边界层控制装置，其适于在表面的选定区域中改变边界层内的至少一个流动特性。该系统还包括剪切应力测量系统，该系统包括热膜传感器装置，其具有可应用于所选区域中的表面的至少一个热膜传感器元件。所述至少一个热膜传感器元件连接到风速计电路，所述风速计电路被配置为提供对应于从相关联的热膜传感器到所述流体流的热传递的传感器信号。该系统还包括与风速计布置和边界层控制装置通信的控制模块。控制模块适用于从风速计电路接收和处理传感器信号信号，并向边界层控制装置提供输入信号。

10. 发明申请

US20180346101A1 Thermally Controlled Active Flow Control System 审中-公开
公开(公告)号：US20180346101A1
公开(公告)日：2018-12-06
申请号：US16102179
申请日：2018-08-13
申请人： The Boeing Company
发明人： Arvin Shmilovich , Edward Andrew Whalen
IPC分类号： B64C21/04 , F15B21/12 , F15C1/00 , B64D33/02
CPC分类号： B64C21/04 , B64C2230/04 , B64C2230/06 , B64C2230/10 , B64C2230/18 , B64D2033/0213 , B64D2033/0226 , F15B21/042 , F15B21/12 , F15B2211/62 , F15B2211/6343 , F15C1/00 , F15D1/008 , F15D1/12 , Y02T50/166 , Y10T137/87265
摘要： A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

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