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41. 发明授权

US10875658B2 Ejector and airfoil configurations 有权
公开(公告)号：US10875658B2
公开(公告)日：2020-12-29
申请号：US16031586
申请日：2018-07-10
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
IPC分类号： B64C23/00 , B64D33/04 , B64C39/02 , B64C15/14 , B64C9/38 , B64C15/00 , B64C21/00 , B64D27/10 , B64C21/04 , F02K1/36 , F02K1/00 , F02C3/04 , F02C6/04 , B64D27/18 , B64D29/02 , B64D33/02
CPC分类号： B64D33/04 , B64C9/38 , B64C15/00 , B64C15/14 , B64C21/00 , B64C21/04 , B64C23/005 , B64C39/024 , B64D27/10 , B64D27/18 , B64D29/02 , B64D33/02 , F02C3/04 , F02C6/04 , F02K1/002 , F02K1/36 , B64C2201/10 , B64C2201/104 , B64C2230/04 , B64C2230/16 , B64D2033/0273 , F05D2220/90 , Y02T50/10 , Y02T50/30 , Y02T50/40
摘要： A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

42. 发明申请

US20060099122A1 Method and device for generating mixtures of fluids in a boundary layer 审中-公开
标题翻译：用于在边界层中产生流体混合物的方法和装置
公开(公告)号：US20060099122A1
公开(公告)日：2006-05-11
申请号：US10536300
申请日：2003-11-25
申请人： Nikolaus Vida
发明人： Nikolaus Vida
IPC分类号： B01D53/94
CPC分类号： F15D1/12 , B63B1/34 , B63B13/02 , B63B2001/345 , B63B2001/385 , B63B2001/387 , B64C21/00 , B64C2230/16 , F15D1/005 , Y02T50/166 , Y02T70/121 , Y02T70/122 , Y02T70/123
摘要： A method and a device to generate an area of a mixture of fluids by introducing media having at least a different physical or chemical property into a boundary layer of a surface using vortices are provided. The method and the device can be applied to moving vehicles or walls of containers surrounding streaming fluids, the fluids being especially mixtures of gases, liquids or combinations of gases and liquids.
摘要翻译：提供了一种通过将具有至少不同的物理或化学特性的介质引入到表面的边界层中以产生流体混合物的区域的方法和装置。该方法和装置可以应用于移动的车辆或围绕流动流体的容器的壁，该流体特别是气体，液体或气体和液体的组合的混合物。

43. 发明申请

US20040253116A1 Aerofoil with gas discharge 失效
标题翻译：机油与气体排放
公开(公告)号：US20040253116A1
公开(公告)日：2004-12-16
申请号：US10477257
申请日：2004-06-17
发明人： Graham Bond Grove
IPC分类号： B63H001/26
CPC分类号： B64C21/04 , B64C3/48 , B64C2230/04 , B64C2230/16 , B64C2230/28 , Y02T50/14 , Y02T50/166 , Y10S416/05
摘要： Upper surface (13) of an aerofoil (or rotor blade) is provided with nozzles or slots (14, 16) at leading portion (15) and trailing portion (17) to assist attachment of airflow by discharging gas towards trailing edge (11). Gas discharged may be heated, eg coming from rocket-type combustion chambers within the aerofoil. The aerofoil may be adjustable between high profile (as shown) and low profile (for supersonic flight) using jacks that pivot sections of upper surface (13) at leading and trailing edges (10-11).
摘要翻译：机翼（或转子叶片）的上表面（13）在引导部分（15）和尾部部分（17）处设置有喷嘴或狭槽（14,16），以通过向后缘（11）排放气体来辅助气流附着，。排出的气体可能被加热，例如来自机翼内的火箭式燃烧室。机翼可以使用在前缘和后缘（10-11）上枢转上表面（13）的部分的千斤顶在高廓（如图所示）和低轮廓（用于超音速飞行）之间可调节。

44. 发明授权

US06682022B2 Boundary layer control of aerodynamic airfoils 有权
标题翻译：空气动力学翼型的边界层控制
公开(公告)号：US06682022B2
公开(公告)日：2004-01-27
申请号：US10286865
申请日：2002-11-04
申请人： Lorenzo Battisti
发明人： Lorenzo Battisti
IPC分类号： B64C2104
CPC分类号： F01D25/12 , B64C21/025 , B64C21/04 , B64C21/06 , B64C2230/04 , B64C2230/16 , B64C2230/20 , B64C2230/22 , B64C2230/28 , C25D1/08 , F01D5/145 , F01D5/183 , F04D29/324 , F04D29/682 , F04D29/684 , Y02T50/166 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： Boundary layer control of a structural element in fluid stream is achieved by the following operations: providing in such structural element at least one region equipped with micro porous structure by an electroforming technique; having a fluid stream flow through the external surface of the at least one region, inwards or outwards with respect to the environment in which that element is placed.
摘要翻译：通过以下操作来实现流体流中的结构元件的边界层控制：通过电铸技术在这种结构元件中提供装配有微孔结构的至少一个区域;使流体流流过至少一个区域，向内或向外相对于放置元素的环境。

45. 发明授权

US06334753B1 Streamlined bodies with counter-flow fluid injection 有权
标题翻译：流动性流体注射流体
公开(公告)号：US06334753B1
公开(公告)日：2002-01-01
申请号：US09629580
申请日：2000-07-31
申请人： Thomas G. Tillman , Brian E. Wake
发明人： Thomas G. Tillman , Brian E. Wake
IPC分类号： F01D2524
CPC分类号： F01D5/186 , B64C21/04 , B64C2230/04 , B64C2230/06 , B64C2230/16 , B64C2230/28 , B64D2033/0226 , F01D5/145 , F05D2250/314 , Y02T50/166 , Y02T50/673 , Y02T50/676 , Y10S415/914
摘要： A streamlined body has oppositely facing external pressure and suction surfaces that meet to form a leading edge region. Passageways within the body direct pressurized fluid from passageway outlets over the pressure surface toward the leading edge region at a shallow angle with respect to the pressure surface. The pressurized fluid travels around the leading edge region to the suction surface, energizing the boundary layer on the suction surface.
摘要翻译：流线型的主体具有相反的外部压力和吸力表面，以形成前缘区域。身体内的通道将压力表面上的通道出口的加压流体相对于压力表面以较小的角度朝向前缘区域引导。加压流体围绕前缘区域传播到吸力表面，激励吸力表面上的边界层。

46. 发明授权

US6123145A Synthetic jet actuators for cooling heated bodies and environments 失效
标题翻译：用于冷却加热体和环境的合成射流致动器
公开(公告)号：US6123145A
公开(公告)日：2000-09-26
申请号：US970607
申请日：1997-11-14
申请人： Ari Glezer , Mark G. Allen
发明人： Ari Glezer , Mark G. Allen
IPC分类号： B64C21/08 , B64G1/26 , B64G1/40 , F01D5/14 , F02K1/28 , F15C1/14 , F15C5/00 , F15D1/08 , F15D1/12 , F16K99/00 , F23R3/24 , H01L23/433 , H05K7/20 , F28D15/00
CPC分类号： F21V29/70 , B64C21/08 , B64G1/26 , B64G1/40 , B64G1/401 , F01D5/148 , F02K1/28 , F15C1/14 , F15C5/00 , F15D1/009 , F15D1/08 , F15D1/12 , F16K99/0001 , F16K99/0007 , F16K99/0048 , F21V29/006 , F21V29/40 , F21V29/402 , F21V29/677 , F21V29/74 , F21V29/83 , F23R3/24 , H01L23/4336 , H05K7/20172 , B64C2230/02 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/16 , B64C2230/18 , F16K2099/0094 , F16K2099/0098 , F16K99/0034 , F28F13/02 , H01L2924/0002 , H01L2924/3011 , Y02T50/166
摘要： Briefly described, the present invention is concerned with cooling heated bodies and/or heated fluid with synthetic jet actuators in either open or closed systems. A first preferred embodiment of a cooling system of the present invention comprises a synthetic jet actuator directed to impinge directly on a heat producing (or heated) body. The synthetic jet actuator generates a synthetic jet stream comprised of cool ambient fluid that impinges on the heated surface thereby cooling this surface. As an example, the heated surface/body could be a microchip array in a microcomputer. After coming into contact with the heated surface, the fluid moves along the surface and is finally rejected to the ambient where it mixes and cools down. The synthetic jet may be incorporated into a modular unit that may be clipped on to a circuit board or other heat producing element to provide added, `ad hoc` cooling. In another configuration, a synthetic jet actuator may be positioned, relative to the heated surface, to create a synthetic jet stream to flow along the heated surface. In this embodiment, the flow would be approximately tangential to a surface of a heat producing body. This embodiment may further comprise a cyclical flow of the fluid jet, along the heated body and about a heat sink surface.
摘要翻译：简要描述，本发明涉及用合成射流致动器在开放或封闭系统中冷却加热体和/或加热流体。本发明的冷却系统的第一优选实施例包括合成射流致动器，其被定向于直接冲击发热（或加热）的主体。合成射流致动器产生合成喷射流，其由暴露在加热表面上的冷的环境流体组成，从而冷却该表面。作为示例，加热表面/主体可以是微型计算机中的微芯片阵列。在与加热表面接触后，流体沿着表面移动，最终被排斥到环境中，在那里它混合并冷却。合成射流可以结合到模块化单元中，该模块单元可以被夹在电路板或其它发热元件上以提供附加的“特别”冷却。在另一种构造中，合成射流致动器可以相对于被加热的表面定位，以产生合成射流以沿加热表面流动。在该实施例中，流动将与发热体的表面大致相切。该实施例还可以包括流体射流沿着被加热体并围绕散热器表面的周期性流动。

47. 发明授权

US5957413A Modifications of fluid flow about bodies and surfaces with synthetic jet actuators 失效
标题翻译：用合成射流致动器改变物体和表面的流体流动
公开(公告)号：US5957413A
公开(公告)日：1999-09-28
申请号：US869374
申请日：1997-06-05
申请人： Ari Glezer , Barton L. Smith , Mark A. Trautman
发明人： Ari Glezer , Barton L. Smith , Mark A. Trautman
IPC分类号： B64C21/08 , B64G1/26 , B64G1/40 , F01D5/14 , F02K1/28 , F15C1/14 , F15C5/00 , F15D1/08 , F15D1/12 , F16K99/00 , F23R3/24 , H01L23/433 , H05K7/20 , B64C21/06
CPC分类号： F21V29/70 , B64C21/08 , B64G1/26 , B64G1/40 , B64G1/401 , F01D5/148 , F02K1/28 , F15C1/14 , F15C5/00 , F15D1/009 , F15D1/08 , F15D1/12 , F16K99/0001 , F16K99/0007 , F16K99/0048 , F21V29/40 , F21V29/63 , F21V29/677 , F21V29/83 , F23R3/24 , H01L23/4336 , H05K7/20172 , B64C2230/02 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/16 , B64C2230/18 , F16K2099/0094 , F16K2099/0098 , F16K99/0034 , F28F13/02 , H01L2924/0002 , H01L2924/3011 , Y02T50/166 , Y02T50/673
摘要： The present invention involves a system for altering the aerodynamic shape and/or fluid flow field about a solid body. The preferred embodiment comprises a synthetic jet actuator embedded in a solid body, with the jet orifice built into the body surface. The synthetic jet actuator generates a series of fluid vortices emanating from the orifice so as to entrain fluid external to the actuator chamber and form a synthetic jet stream. A recirculating flow region is formed along the solid body surface about the synthetic jet orifice. As a result the apparent aerodynamic shape of the body is altered. Consequently, if the solid body is placed in a fluid flow field, the entire fluid flow field is altered by the operation of the synthetic jet actuator.
摘要翻译：本发明涉及一种用于改变围绕固体的空气动力学形状和/或流体流场的系统。优选实施例包括嵌入固体中的合成射流致动器，喷射孔内置于体表中。合成射流致动器产生从孔口发出的一系列流体涡流，以便将致动器室外的流体夹带并形成合成射流。沿合成射流孔的固体表面形成再循环流动区域。结果，身体的明显的空气动力学形状被改变。因此，如果将固体放置在流体流场中，则通过合成射流致动器的操作来改变整个流体流场。

48. 发明授权

US5927645A Shovel nose pneumatic vortex control 失效
标题翻译：铲鼻气动涡流控制
公开(公告)号：US5927645A
公开(公告)日：1999-07-27
申请号：US7717
申请日：1998-01-15
申请人： John Paul Latz
发明人： John Paul Latz
IPC分类号： B64C23/06 , B64C7/00
CPC分类号： B64C23/06 , B64C2230/04 , B64C2230/06 , B64C2230/16 , Y02T50/162 , Y02T50/166
摘要： A system for facilitating the enhanced aerodynamic control of an aircraft having a fuselage including a forebody defining a frontal portion adapted to create a primary vortex under certain flight conditions and a rear portion. The control system comprises a contour discontinuity which is formed between the frontal and rear portions of the forebody. The contour discontinuity is sized and configured to create a secondary vortex under certain flight conditions. In addition to the contour discontinuity, the control system comprises a pressurized fluid injecting device which is disposed within the forebody of the fuselage adjacent the contour discontinuity. The pressurized fluid injecting device is used to selectively manipulate the secondary vortex to control the flight performance characteristics of the aircraft.
摘要翻译：一种用于促进具有机身的飞机的增强的空气动力学控制的系统，其包括限定适于在某些飞行条件下产生初级涡流的前部的前体和后部。控制系统包括形成在前体的前部和后部之间的轮廓不连续部。轮廓不连续的尺寸和构造可在某些飞行条件下产生二次涡流。除了轮廓不连续性之外，控制系统还包括加压流体喷射装置，该加压流体喷射装置设置在与机体不连续性相邻的机身前体内。加压流体注入装置用于选择性地操纵二次涡流以控制飞行器的飞行性能特征。

49. 发明授权

US5114102A Boundary layer control 失效
标题翻译：边界层控制
公开(公告)号：US5114102A
公开(公告)日：1992-05-19
申请号：US417910
申请日：1989-10-06
申请人： Timothy Wang
发明人： Timothy Wang
IPC分类号： B64C21/04
CPC分类号： B64C21/04 , B64C2230/04 , B64C2230/16 , Y02T50/166
摘要： Methods of and apparatus for controlling the separation of a boundary layer from a surface on which an adverse pressure gradient exists. A streamwise jet of fluid is so discharged onto the surface at a location adjacent the juncture between the surface and an adjoining structure as to energize the boundary layer and thereby delay the separation of the boundary layer from the airfoil in the vicinity of that juncture.
摘要翻译：用于控制边界层与存在不利压力梯度的表面分离的方法和装置。流体流的流体在与表面和相邻结构之间的接合处相邻的位置处被排出到表面上，以激励边界层，从而延迟边界层在该接合处附近与翼型的分离。

50. 发明授权

US4976349A Aerofoil/hydrofoil 失效
标题翻译：机翼/水翼
公开(公告)号：US4976349A
公开(公告)日：1990-12-11
申请号：US201177
申请日：1988-06-02
申请人： Richard C. Adkins
发明人： Richard C. Adkins
IPC分类号： B64C9/38 , B64C21/04
CPC分类号： B64C21/04 , B64C9/38 , B64C2230/04 , B64C2230/06 , B64C2230/16 , Y02T50/166
摘要： An aerofoil or hydrofoil (1) has a vessel (2) for providing a high velocity jet of fluid directed from a nozzle (3) in a direction having a component of velocity in the same direction as the required direction of lift (L). The aerofoil or hydrofoil (1) also has a curved surface (5) convex on the side of the aerofoil or hydrofoil which is in the direction of the required lift, and which serves to direct the velocity of the jet in a direction which is substantially opposite to the direction of the required lift or thrust force, the primary jet being directed over the convex surface for attachment thereto; and a duct formed over a rear part of the convex surface remote from the nozzle, whereby the primary jet of fluid flowing over and attached to the convex surface causes an enhanced flow through the duct, the duct being directed at least at its exit end in a direction so that the flow therethrough has a component of velocity opposite that of the required direction of lift.

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