| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 用于减少物体在流体中的流动阻力的结构 | CN201180007716.9 | 2011-01-28 | CN102762452A | 2012-10-31 | 马尔科·福西 |
| 本发明涉及一种具有流体（30）能够流过的至少一个表面（12）的物体（10），所述表面具有限定流过所述表面（12）的主流动方向（14）的球状路径。所述表面（12）至少局部地具有用于减少所述物体（10）的流动阻力的结构，所述结构具有用于引起流体涡流（26.2、26.3）的至少一个凹部（16.2、16.3），凹部设置为大致圆弧段状横截面。所述物体的特征在于，所述结构具有用于将流体流（24）引导入所述凹部（16.2、16.3）的至少一个导入部（18.2、18.3），导入部朝着凹部（16.2、16.3）的方向与主流动方向成角度，并且在主流动方向上布置在凹部（16.2、16.3）的上游。借助所述结构，能够在凹部（16.2、16.3）内引起流体涡流（26.2、26.3）并且能够使流体涡流大致集中在凹部（16.2、16.3）内。 | ||||||
| 2 | 大气压反重力装置 | CN201610535732.X | 2016-07-09 | CN106516108A | 2017-03-22 | 王金海 |
| 本发明涉及一种反重力装置。大气压反重力装置，包括储运仓，储运仓上表面设置为弧形表面，储运仓上方或上部设置有高压空气室，高压空气室的进气口连通N个风机或空气压缩机，高压空气室设置有N个出气口，出气口设置有与之相连通的并列的N个喷射管道。本发明通过喷射高压空气室内的高压气体，使高压气体在储运仓的上表面形成高速空气流，使得空气对储运仓的垂直向下的压力降低。最终本发明向上的升力大于向下的力，使得本发明实现上升的功能。 | ||||||
| 3 | 用于减小因物体与流体相对移动而产生的阻力的装置 | CN200680045765.0 | 2006-12-05 | CN101374717A | 2009-02-25 | Y·布鲁哈特 |
| 一种用于减小因物体和流体之间或流体在物体中的相对运动而产生的阻力或水头损失的装置。在与流体接触的物体的表面内或在该表面顶部，所述装置具有用于对沿物体表面的流体旋涡的旋转方向进行控制的部件(2)，因而减小了流体与物体之间的摩擦力，并因此减小了阻力、物体所受到的限制、或流体的水头损失。 | ||||||
| 4 | 流体中の本体の流動抵抗を低減するための構造 | JP2012550284 | 2011-01-28 | JP5926689B2 | 2016-05-25 | マルコ・フォイジ |
| 5 | Acoustic jet, which is passively drive to control the boundary layer | JP2000600893 | 2000-02-25 | JP2002537184A | 2002-11-05 | シー． マコーミック，デュアン; ケイ． ロード，ウェスレイ |
| Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle of which directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, or a duct, the fluid particles in the resonant chamber of the passive acoustic jet being replenished with low momentum flux particles drawn from the fluid flow in a direction normal to the surface, thereby to provide a net time averaged flow of increased momentum flux particles to defer, even eliminate, the onset of boundary layer separation in the diffuser or duct. The passive acoustic jet is used in the vicinity of fan blade tips to alleviate undesirable flow effects in the tip region, such as leakage. | ||||||
| 6 | Structure in order to reduce the flow resistance of the body in a fluid | JP2012550284 | 2011-01-28 | JP2013518225A | 2013-05-20 | マルコ・フォイジ |
| The invention relates to a body (10) having at least one surface (12) over which a fluid (30) can flow, said surface having a global course that defines a main flow direction (14) over the surface (12) at least partially has a structure for reducing a flow resistance of the body (10), the structure having at least one recess (16.2 . . . 16.3) provided with a substantially circle-segment-shaped cross-section for inducing a fluid eddy (26.2) . . . 26.3). The body is characterized in that the structure has at least one lead-in section (18.2 . . . 18.3), which is angled from the main flow direction in the direction of the recess (16.2 . . . 16.3) and which is arranged upstream of the recess (16.2 . . . 16.3) in the main flow direction, for leading a fluid flow (24) into the recess (16.2 . . . 16.3). By means of the structure, a fluid eddy (26.2 . . . 26.3) can be induced within the recess (16.2 . . . 16.3) and can be localized substantially within the recess (16.2 . . . 16.3). | ||||||
| 7 | Fluid frictional resistance reducing device of substance | JP199499 | 1999-01-07 | JP2000199505A | 2000-07-18 | UMAZUME KOSUKE; HASHIGUCHI MASAYOSHI |
| PROBLEM TO BE SOLVED: To sufficiently reduce a fluid frictional resistance by providing a groove receiving fluid moving along a surface of a substance relatively moving in fluid to turning the same to a moving direction, at the surface thereof. SOLUTION: A substance B has at its surface S a groove M receiving fluid moving along the surface S and turning the same to a moving direction X. Thereby at a bottom of the groove M a reverse flow generates when fluid is turned into the flow direction X so that a primary gradient of speed component in the flow direction X of fluid becomes negative, and also an absolute value in the primary gradient of the fluid speed component in a groove M area can be reduced. The groove M is provided across the whole surface S of the substance B or provided partially or in a continuously extending manner or intermittently with short ones, or an arbitral combination of the long and short ones. The direction should be that crossing the fluid flow direction S. COPYRIGHT: (C)2000,JPO | ||||||
| 8 | 동체 및 유체의 상대 변위에 의해 발생된 항력을감소시키는 장치 | KR1020087013696 | 2006-12-05 | KR1020080081915A | 2008-09-10 | 브룰하트이반 |
| A device reduces a drag, and thereby a pressure loss, produced by a relative displacement between a body and a fluid or a fluid displacement in the body. The inventive device comprises means (2) which is arranged in or on the body surface contacting with the fluid along said surface for controlling the direction of rotation of the fluid swirls, thereby reducing friction forces between said body and fluid, the drag, the stresses to which the body is exposed or the fluid pressure loss. | ||||||
| 9 | Core cowl for a turbofan engine | US14476685 | 2014-09-03 | US10094332B2 | 2018-10-09 | David F. Cerra; Paul Robert Tretow; Robert H. Willie; Abhishek Sahay |
| A core cowl for a turbofan engine may include a plurality of valleys formed in an outer surface of the core cowl. Each valley may include a convex portion upstream of a concave portion, and may be configured to disrupt a shock cell exiting a fan nozzle of the turbofan engine. Associated methods for reducing turbofan engine noise are also described. | ||||||
| 10 | Load compensating devices | US14681703 | 2015-04-08 | US09890765B2 | 2018-02-13 | Qing Tian; Jehan Z. Khan; Jonathon P. Baker |
| Various air deflector shapes, sizes and configurations for use in a load compensating device on an airfoil are provided. The air deflector arrangements are configured to alter the airflow around the air deflector in order to affect sound or acoustics associated with the air deflector when deployed during operation. Some example configurations that may alter the air flow around the air deflector include air deflectors having a plurality of apertures, air deflectors including a scalloped edge, and/or air deflectors including a plurality of protrusions extending from a portion of the air deflector. | ||||||
| 11 | Aerodynamic component and method for producing an aerodynamic component | US14937220 | 2015-11-10 | US09745053B2 | 2017-08-29 | Benjamin Teich |
| An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough. | ||||||
| 12 | AERODYNAMIC COMPONENT AND METHOD FOR PRODUCING AN AERODYNAMIC COMPONENT | US14937220 | 2015-11-10 | US20160137292A1 | 2016-05-19 | Benjamin TEICH |
| An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough. | ||||||
| 13 | CORE COWL FOR A TURBOFAN ENGINE | US14476685 | 2014-09-03 | US20160061115A1 | 2016-03-03 | David F. Cerra; Paul Robert Tretow; Robert H. Willie; Abhishek Sahay |
| A core cowl for a turbofan engine may include a plurality of valleys formed in an outer surface of the core cowl. Each valley may include a convex portion upstream of a concave portion, and may be configured to disrupt a shock cell exiting a fan nozzle of the turbofan engine. Associated methods for reducing turbofan engine noise are also described. | ||||||
| 14 | CAVITY ACOUSTIC TONES SUPPRESSION | US14775832 | 2014-03-13 | US20160031386A1 | 2016-02-04 | David Euan Patience |
| A cavity system that tends to increase the thickness (28) of the shear layer (22), comprising: a cavity (2) and a plurality of rods (4) extending away from the cavity base (3) to a height extending beyond the leading edge (14); the rods (4) being positioned downstream of and in the proximity of the leading edge (14). The rods (4) may extend to different heights and/or be positioned longitudinally offset (e.g. in a zig-zag pattern). The rods may be reversibly movable to a configuration in which they are fully enclosed in the cavity (2) when the cavity (2) is closed. Flow alteration elements (34, 38), for example channels (34) passing through the rods (4) and/or protrusions (38) extending from the rod (4) may be provided on the rods (4). | ||||||
| 15 | STRUCTURE FOR REDUCING A FLOW RESISTANCE OF A BODY IN A FLUID | US13575137 | 2011-01-28 | US20120312930A1 | 2012-12-13 | Marco Feusi |
| The invention relates to a body (10) having at least one surface (12) over which a fluid (30) can flow, said surface having a global course that defines a main flow direction (14) over the surface (12) at least partially has a structure for reducing a flow resistance of the body (10), the structure having at least one recess (16.2 . . . 16.3) provided with a substantially circle-segment-shaped cross-section for inducing a fluid eddy (26.2) . . . 26.3). The body is characterized in that the structure has at least one lead-in section (18.2 . . . 18.3), which is angled from the main flow direction in the direction of the recess (16.2 . . . 16.3) and which is arranged upstream of the recess (16.2 . . . 16.3) in the main flow direction, for leading a fluid flow (24) into the recess (16.2 . . . 16.3). By means of the structure, a fluid eddy (26.2 . . . 26.3) can be induced within the recess (16.2 . . . 16.3) and can be localized substantially within the recess (16.2 . . . 16.3). | ||||||
| 16 | High performance synthetic valve/pulsator | US11508469 | 2006-08-23 | US07748664B2 | 2010-07-06 | Matthew Patrick Boespflug; Seyed Gholamali Saddoughi |
| A system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a dual diaphragm synthetic jet coupled to high performance dual actuator solenoids, wherein the synthetic jet is operable to produce an oscillatory flow. The oscillatory flow of the synthetic jet(s) produces the pulsed jet operable to manipulate the primary fluid flow. These synthetic pulsators may then be 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. | ||||||
| 17 | Flow-driven oscillating acoustic attenuator | US12008134 | 2008-01-09 | US20090045289A1 | 2009-02-19 | Alan J. Bilanin; Todd J. Quackenbush; Pavel V. Danilov |
| An apparatus for attenuating acoustic resonance generated by flow over a cavity in a surface comprises a plurality of flat flaps proximate to an upstream edge of the cavity. The flaps are disposed in an array spaced in a width direction of the cavity edge, and are oscillated by the flow in two degrees of freedom solely by the flow, independent of an actuation mechanism. Each flap includes a first hinge generally coextensive with the surface for enabling oscillation in a first degree of freedom and a second hinge orthogonal to the first hinge and forming a tab for enabling oscillation in a second degree of freedom. The hinges are constructed with torsional spring constants that provide predetermined oscillation frequencies and magnitudes. The apparatus can include a deployment mechanism for moving each flap between a stowed position wherein it is generally flush with the surface and a deployed position wherein the flap can be oscillated by the flow. | ||||||
| 18 | High performance synthetic valve/pulsator | US11508469 | 2006-08-23 | US20080087771A1 | 2008-04-17 | Matthew Patrick Boespflug; Seyed Gholamali Saddoughi |
| The present invention provides a system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a dual diaphragm synthetic jet coupled to high performance dual actuator solenoids, wherein the synthetic jet is operable to produce an oscillatory flow. The oscillatory flow of the synthetic jet(s) produces the pulsed jet operable to manipulate the primary fluid flow. These synthetic pulsators may then be 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. | ||||||
| 19 | Oscillating vane actuator apparatus and method for active flow control | US11498090 | 2006-08-03 | US07246529B1 | 2007-07-24 | Arthur Gregory Powell |
| An oscillating vane actuator for active control of fluid flow over a surface includes a pivoted vane surrounded by a wedge-shaped chamber, and first and second conduits with openings adjacent the surface. The actuator also includes a rotating shaft with a connecting rod to actuate the vane in a oscillatory manner. As the vane travels in one direction, fluid is forced out from the chamber through the first conduit and opening into the fluid stream adjacent the surface, while fluid is simultaneously drawn in through the second opening and conduit into the opposite side of the chamber. Similarly, when the vane travels in the opposite direction, fluid is forced out through the second conduit and opening into the fluid stream adjacent the surface, while fluid is simultaneously drawn in through the first opening and conduit. | ||||||
| 20 | Method and apparatus for control of shock/boundary-layer interactions | US10170225 | 2002-06-12 | US06651935B2 | 2003-11-25 | Eric Loth; Philippe H. Geubelle; Scott R. White; Andrew G. Alleyne; Stephen T. Mcllwain; J. Craig Dutton; Daniel Tortorelli; David Davis |
| Apparatus for controlling shock/boundary-layer interactions created by a supersonic shock on a surface of a structure, includes a cavity formed in the structure and having an opening on the surface. A plate is attached to the surface and covers the opening. A plurality of flaps are formed on the plate and is operable to cooperatively close the opening in response to subsonic airflow condition over the flaps, and open the opening to permit airflow through the cavity in response to supersonic airflow conditions over the flaps. | ||||||
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