公开(公告)号：EP2086831B1

公开(公告)日：2013-07-03

申请号：EP07866478.6

申请日：2007-10-31

申请人： Centre National de la Recherche Scientifique

发明人： STANISLAS, Michel ,  FOUCAUT, Jean-Marc ,  KOSTAS, Dimitrios ,  DYMENT, Arthur

IPC分类号： B64C21/04

CPC分类号： B64C21/08 ,  B64C21/04 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/18 ,  F15D1/12 ,  Y02T50/166

公开(公告)号：EP2268541B1

公开(公告)日：2012-07-04

申请号：EP09731423.1

申请日：2009-04-07

申请人： Airbus Operations GmbH

发明人： LORKOWSKI, Thomas

IPC分类号： B64C21/02 ,  B64C21/08

CPC分类号： B64C21/04 ,  B64C21/08 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/18 ,  B64C2230/22 ,  Y02T50/166

摘要： Disclosed is a flow element (1) comprising an external side (3) that has a top face (3a) and a bottom face (3b) in relation to the direction of flow, and lateral end sections (5a, 5b) that form the lateral ends of the flow element (1) transversal to the theoretical direction of flow (S). A duct (10) is arranged inside the flow element (1). Said duct (10) encompasses a flow drive with a driving motor and a compressor means which is driven by the driving motor and is disposed in the duct (10). The duct (10) has at least one inlet (11) on the bottom face (3b) and/or on at least one of the lateral end sections (5a, 5b) of the flow element (1) as well as an outlet (12) on the top face (3a) of the flow element (1) in order to influence the flow on the flow element (1). A sleeve (30) that can be rotated by means of the driving motor is located inside the duct (10). Said sleeve (30) has at least one cavity (33) which can be made to at least partially overlap with the outlet (12) on the top face (3a) of the flow element (1) in a specific rotational position of the sleeve (30) such that the air that is compressed by the compressor flows through the cavity (33) of the sleeve (30) and the outlet (12). A high-lift system comprising such a flow element is also disclosed.

公开(公告)号：EP1907279B1

公开(公告)日：2011-03-16

申请号：EP06764945.9

申请日：2006-07-13

申请人： City University

发明人： PRINCE, Simon Andrew, Centre for Aeronautics ,  KHODAGOLIAN, Vahik, Centre for Aeronautics

IPC分类号： B64C21/04

CPC分类号： B64C23/06 ,  B64C2230/06 ,  B64C2230/18 ,  B64C2230/20 ,  F03D1/0641 ,  F05D2240/30 ,  Y02E10/721 ,  Y02T50/162 ,  Y02T50/166

摘要： This invention relates to an element (11) for generating a fluid dynamic force, the element (11) comprising first (13) and second (15) surfaces extending in opposite directions from a leading edge (17) of the element (11) and meeting at a trailing edge (18) thereof to define a three dimensional body that is shaped to generate a fluid dynamic force when immersed at an angle of attack α to a fluid flow over the element (11) in a flow direction U, the first surface (13) comprising an array of fluid inlets (19) and the second surface (15) comprising a corresponding array of fluid outlets (21), each said inlet (19) being fluidly coupled to a said outlet (21) by means of a fluid duct (23) at least part of which is pitched at an angle θ to a tangent plane (Y-Y) to said second surface (15) in the vicinity of said outlet (21) and skewed at an angle φ to said fluid flow direction U, the arrangement being such that the element (11) is operable in use to generate a relatively high fluid pressure region downstream of said leading edge (17) proximate said first surface (13) and a relatively low fluid pressure region downstream of said leading edge (17) proximate said second surface (15), and fluid from said relatively high fluid pressure region is enabled to flow into said fluid inlets (19) through said fluid ducts (23) and out of said fluid outlets (21) into said relatively low pressure region to generate fluid vortices which reenergise said low pressure region and delay boundary layer separation from said second surface (15).

公开(公告)号：EP1931566B1

公开(公告)日：2010-09-08

申请号：EP06851665.7

申请日：2006-07-26

申请人： The Boeing Company

发明人： POWELL, Arthur G.

IPC分类号： B64C21/02

CPC分类号： B64C21/025 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/18 ,  Y02T50/166

公开(公告)号：EP2162342A1

公开(公告)日：2010-03-17

申请号：EP08738244.6

申请日：2008-04-27

申请人： Ramot at Tel-Aviv University Ltd.

发明人： SEIFERT, Avraham ,  PALEI, Vitali

IPC分类号： B62D35/00

CPC分类号： B62D35/00 ,  B64C2230/18 ,  F15D1/12 ,  Y02T50/166 ,  Y10T137/0318 ,  Y10T137/0391 ,  Y10T137/206 ,  Y10T137/2202 ,  Y10T137/2234 ,  Y10T137/2245

摘要： A method of reducing aerodynamic drag on a moving blunt-edged body, the method comprising actively generating a flow of air at a blunt edge of a body and using the generated flow of air to control an external flow of air moving relative to an edge of a moving blunt-body.

公开(公告)号：EP1907279A1

公开(公告)日：2008-04-09

申请号：EP06764945.9

申请日：2006-07-13

申请人： City University

发明人： PRINCE, Simon Andrew, Centre for Aeronautics ,  KHODAGOLIAN, Vahik, Centre for Aeronautics

IPC分类号： B64C23/06

CPC分类号： B64C23/06 ,  B64C2230/06 ,  B64C2230/18 ,  B64C2230/20 ,  F03D1/0641 ,  F05D2240/30 ,  Y02E10/721 ,  Y02T50/162 ,  Y02T50/166

摘要： This invention relates to an element (11) for generating a fluid dynamic force, the element (11) comprising first (13) and second (15) surfaces extending in opposite directions from a leading edge (17) of the element (11) and meeting at a trailing edge (18) thereof to define a three dimensional body that is shaped to generate a fluid dynamic force when immersed at an angle of attack α to a fluid flow over the element (11) in a flow direction U, the first surface (13) comprising an array of fluid inlets (19) and the second surface (15) comprising a corresponding array of fluid outlets (21), each said inlet (19) being fluidly coupled to a said outlet (21) by means of a fluid duct (23) at least part of which is pitched at an angle θ to a tangent plane (Y-Y) to said second surface (15) in the vicinity of said outlet (21) and skewed at an angle φ to said fluid flow direction U, the arrangement being such that the element (11) is operable in use to generate a relatively high fluid pressure region downstream of said leading edge (17) proximate said first surface (13) and a relatively low fluid pressure region downstream of said leading edge (17) proximate said second surface (15), and fluid from said relatively high fluid pressure region is enabled to flow into said fluid inlets (19) through said fluid ducts (23) and out of said fluid outlets (21) into said relatively low pressure region to generate fluid vortices which reenergise said low pressure region and delay boundary layer separation from said second surface (15).

公开(公告)号：EP1544089B1

公开(公告)日：2008-01-16

申请号：EP04028097.6

申请日：2004-11-26

申请人： C.R.F. Società Consortile per Azioni

发明人： Casella, Mauro ,  Tregnago, Roberto

IPC分类号： B62D37/02 ,  B62D35/00

CPC分类号： B62D35/001 ,  B62D37/02 ,  B64C2230/02 ,  B64C2230/18 ,  Y02T50/166

公开(公告)号：EP1633625A1

公开(公告)日：2006-03-15

申请号：EP04736408.8

申请日：2004-06-09

申请人： BAE Systems PLC

发明人： WARSOP, Clyde, BAE Systems ATC Sowerby ,  WATSON, Mark, Manchester School of Engineering ,  JAWORSKI, Artur J., Manchester Sch. of Engineering

IPC分类号： B64C23/06

CPC分类号： B64C23/06 ,  B64C2230/02 ,  B64C2230/18 ,  Y02T50/162 ,  Y02T50/166

摘要： This invention relates to a method of controlling vortex bursting on an aerodynamic surface (20) associated with separated flows and, in particular, relates to control of separated flows over aerodynamic or hydrodynamic surfaces (20) that may have highly swept leading edges (26). A method of controlling vortex bursting on an aerodynamic surface or a hydrodynamic surface (20) is provided, the surface (20) comprising a gas source (22) located on or in the surface (20) and the method comprising the step of repeatedly operating the gas source (22) thereby to eject a flow of gas into an airflow passing over the surface (20). Effective control of the frequency at which the gas source (22) is operated has been found to reduce pressures on the surface (20) caused by vortex bursting. The present invention also provides a synthetic jet actuator (22) and an aerodynamic or hydrodynamic surface (20) comprising a plurality of such discrete synthetic jet actuators (22).

摘要翻译： 本发明涉及一种控制与分离流相关联的空气动力学表面（20）上的涡流爆裂的方法，并且具体地涉及对可能具有高度扫过的前缘（26）的空气动力学或流体动力学表面（20） 。 提供了一种控制空气动力学表面或流体动力学表面（20）上的涡流爆裂的方法，所述表面（20）包括位于所述表面（20）上或其中的气体源（22），并且所述方法包括重复操作 所述气源（22）由此将气流喷射到在所述表面（20）上方通过的气流中。 已经发现有效控制气体源（22）工作的频率可以降低由涡流破裂引起的表面（20）上的压力。 本发明还提供一种合成射流致动器（22）以及包括多个这种离散合成射流致动器（22）的空气动力学或流体动力学表面（20）。

公开(公告)号：EP1623922A1

公开(公告)日：2006-02-08

申请号：EP05425549.2

申请日：2005-07-27

申请人： Lockheed Martin Corporation

发明人： Miller, Daniel N. ,  Yagle, Partick J. ,  Truax, Philip P.

IPC分类号： B64C21/04 ,  B64C23/00

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 (32) within a fluid flow (14) over a surface (16) using micro-jet arrays (10). The system and method for actively manipulating and controlling the inception point, size and trajectory of flow field vortices (32) within the fluid flow (14) places micro-jet arrays (10) on surfaces bounding the fluid flow (14). These micro-jet arrays (10) are then actively manipulated to control the flow behavior of the ducted fluid flow (14), influence the inception point and trajectory of flow field vortices (32) within the fluid flow (14), and reduce flow separation within the primary fluid flow (14).

摘要翻译： 本发明提供一种用于使用微喷射阵列（10）主动地操纵和控制在表面（16）上的流体流（14）内的空气动力学或流体动力学流动涡旋（32）的系统和方法。 用于主动地操纵和控制流体流（14）内的流场涡流（32）的起始点，大小和轨迹的系统和方法将微喷射阵列（10）放置在界定流体流（14）的表面上。 然后主动地操纵这些微喷射阵列（10）以控制管道流体流（14）的流动行为，影响流体流（14）内的流场涡流（32）的起始点和轨迹，并减少流动 主流体流（14）内的分离。

公开(公告)号：EP3318485A1

公开(公告)日：2018-05-09

申请号：EP17187296.3

申请日：2017-08-22

申请人： The Boeing Company

发明人： Brzozowski, Daniel Paul ,  Griffin, Steven Fulton

IPC分类号： B64C21/08 ,  F15D1/00

CPC分类号： F15D1/0095 ,  B64C21/08 ,  B64C23/06 ,  B64C2230/04 ,  B64C2230/18 ,  B64D43/02 ,  Y02T50/166

摘要： A device including a resonant array of a plurality of synthetic jet generators where neighboring jet generators are coupled, resulting in the potential for constructive and destructive interference between jets of the plurality of synthetic jet generators depending on the relative phase of a corresponding plurality of drive signals to plurality of synthetic jet generators. The device also includes a controller configured to control the relative phase of the corresponding plurality of drive signals to effect a change in a first jet emitted by a first synthetic jet generator of the plurality of synthetic jets by changing a given phase of a second jet emitted by a second synthetic jet generator of the plurality of synthetic jet generators.

摘要翻译： 包括多个合成射流发生器的共振阵列的装置，其中相邻的射流发生器被耦合，导致多个合成射流发生器的射流之间的相长和相消干涉的可能性取决于相应的多个驱动信号的相对相位 到多个合成射流发生器。 该装置还包括控制器，该控制器被配置为控制相应的多个驱动信号的相对相位，以实现由多个合成射流中的第一合成射流发生器发射的第一射流中的改变，通过改变发射的第二射流的给定相位 通过多个合成射流发生器的第二合成射流发生器。