公开(公告)号：US20170369147A1

公开(公告)日：2017-12-28

申请号：US15535841

申请日：2015-12-09

申请人： BOMBARDIER INC.

发明人： Raymond Lee Man WONG

IPC分类号： B64C1/40 ,  B64C3/18 ,  B64C3/26 ,  B64C21/02

CPC分类号： B64C1/40 ,  B64C3/187 ,  B64C3/26 ,  B64C21/02 ,  B64C2230/08 ,  B64C2230/14 ,  B64C2230/22 ,  B64C2230/24 ,  B64D2033/0206 ,  Y02T50/166

摘要： Sound absorbers and airframe components comprising such sound absorbers are disclosed. In one embodiment, an airframe component comprises an aerodynamic surface (48) and a sound absorber (38). The sound absorber (38) comprises a perforated panel (40) having a front side exposed to an ambient environment outside of the airframe component and an opposite back side. The panel (40) comprises perforations extending through a thickness of the panel for permitting passage of sound waves therethrough. The sound absorber (38) also comprises a boundary surface spaced apart from the perforated panel. The boundary surface and the back side of the perforated panel (40) at least partially define a cavity in the airframe component for attenuating some of the sound waves entering the cavity via the perforations in the perforated panel (40).

公开(公告)号：US09132909B1

公开(公告)日：2015-09-15

申请号：US13838163

申请日：2013-03-15

申请人： The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

发明人： Mehdi R. Khorrami ,  Meelan M. Choudhan

IPC分类号： B64C21/00 ,  B64C1/40

CPC分类号： B64C9/18 ,  B64C21/10 ,  B64C23/005 ,  B64C2230/14 ,  B64C2230/22 ,  B64C2230/24 ,  Y02T50/166 ,  Y02T50/32

摘要： A flap of the type that is movably connected to an aircraft wing to provide control of an aircraft in flight includes opposite ends, wherein at least a first opposite end includes a plurality of substantially rigid, laterally extending protrusions that are spaced apart to form a plurality of fluidly interconnected passageways. The passageways have openings adjacent to upper and lower sides of the flap, and the passageways include a plurality of bends such that high pressure fluid flows from a high pressure region to a low pressure region to provide a boundary condition that inhibits noise resulting from airflow around the end of the flap.

摘要翻译： 可移动地连接到飞行器机翼以提供对飞行器的飞行器的控制的类型的翼片包括相对的端部，其中至少第一相对端包括多个基本上刚性的横向延伸的突出部，其间隔开以形成多个 流体互连的通道。 通道具有邻近翼片的上侧和下侧的开口，并且通道包括多个弯曲部，使得高压流体从高压区域流到低压区域，以提供抑制由于周围气流引起的噪声的边界条件 皮瓣的末端。

公开(公告)号：US07798448B2

公开(公告)日：2010-09-21

申请号：US12008134

申请日：2008-01-09

申请人： Alan J. Bilanin ,  Todd R. Quackenbush ,  Pavel V. Danilov

发明人： Alan J. Bilanin ,  Todd R. Quackenbush ,  Pavel V. Danilov

IPC分类号： B64C23/06

CPC分类号： B64C23/005 ,  B64C2230/08 ,  B64C2230/24 ,  F15D1/10 ,  Y02T50/166

摘要： 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.

摘要翻译： 用于衰减由表面上的腔体上的流动产生的声共振的装置包括靠近空腔的上游边缘的多个平板。 翼片被设置成在空腔边缘的宽度方向上间隔开的阵列中，并且仅通过流动而以两个自由度的流动振荡，而与致动机构无关。 每个翼片包括通常与表面共同延伸的第一铰链，用于使得能够在第一自由度中摆动，而第二铰链与第一铰链正交并形成用于使第二自由度摆动的翼片。 铰链由扭转弹簧常数构成，提供预定的振荡频率和幅度。 该装置可以包括一个展开机构，用于在收集位置之间移动每个折板，其中它与表面大致齐平，并且展开位置，其中翼片可以被流动摆动。

公开(公告)号：US20080217468A1

公开(公告)日：2008-09-11

申请号：US12043157

申请日：2008-03-06

申请人： Thierry FOL

发明人： Thierry FOL

IPC分类号： B64D27/00

CPC分类号： B64C7/02 ,  B64C21/02 ,  B64C2230/08 ,  B64C2230/20 ,  B64C2230/22 ,  B64C2230/24 ,  B64D29/02 ,  Y02T50/166

摘要： A mast for connection between a power plant and the rest of an aircraft that includes an outside surface (14) that is in contact with the air flows, characterized in that it includes, in the outside surface (14), at least one recess (22) that is blocked by a porous wall (24), with a porosity of 3 to 6%, coming into the extension of the outside surface (14), whereby the recess makes it possible to have the high-pressure zone (18) communicate with the low-pressure zone (20), zones that are arranged on both sides of a shock wave (16).

摘要翻译： 一种用于在发电厂和飞行器的其余部分之间连接的桅杆，其包括与空气流动接触的外表面（14），其特征在于，其在所述外表面（14）中包括至少一个凹部（ 22），由多孔壁（24）阻挡，孔隙率为3〜6％，进入外表面（14）的延伸部分，由此该凹槽使得可以具有高压区域（18） 与低压区（20）连通，设置在冲击波（16）两侧的区域。

公开(公告)号：US07305893B2

公开(公告)日：2007-12-11

申请号：US11594122

申请日：2006-11-08

申请人： Arthur Gregory Powell ,  Jay Robert Simmons

发明人： Arthur Gregory Powell ,  Jay Robert Simmons

IPC分类号： G01F1/28

CPC分类号： B64C21/025 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/08 ,  B64C2230/18 ,  B64C2230/24 ,  Y02T50/166

摘要： 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.

公开(公告)号：US09340281B2

公开(公告)日：2016-05-17

申请号：US14448479

申请日：2014-07-31

申请人： The Boeing Company

发明人： Neal A. Harrison ,  Mark Dehaan ,  John C. Vassberg ,  Anthony J. Sclafani

IPC分类号： B64C23/06 ,  B64C1/00 ,  B64C19/00 ,  B64C21/02 ,  F15D1/00

CPC分类号： B64C23/06 ,  B64C1/0009 ,  B64C19/00 ,  B64C21/02 ,  B64C2230/08 ,  B64C2230/20 ,  B64C2230/22 ,  B64C2230/24 ,  F15D1/0025 ,  Y02T50/12 ,  Y02T50/162 ,  Y02T50/166

摘要： A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow.

摘要翻译： 涡流发生器可以包括空气动力学表面中的凹陷和位于凹陷中的涡流发生器前缘。 涡流发生器前缘可以包括前缘上表面。 前缘上表面可以定位在相对于迎面而来的局部流动沿着凹陷上游的空气动力学表面的位置处的切线处或下方。

公开(公告)号：US20120312930A1

公开(公告)日：2012-12-13

申请号：US13575137

申请日：2011-01-28

申请人： Marco Feusi

发明人： Marco Feusi

IPC分类号： B64C23/06

CPC分类号： B64C21/10 ,  B64C2230/08 ,  B64C2230/24 ,  B64C2230/26 ,  Y02T50/166

摘要： 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).

摘要翻译： 本发明涉及一种具有至少一个表面（12）的主体（10），流体（30）可以在该表面上流动，所述表面具有至少在表面（12）上限定主流动方向（14）的全局过程 部分地具有用于降低主体（10）的流动阻力的结构，该结构具有至少一个设置有大致圆弧形截面的凹部（16.2 ... 16.3），用于引导流体涡流（26.2） 。 。 。 26.3）。 该主体的特征在于，该结构具有至少一个导入部分（18.2 ... 18.3），该导入部分从主流动方向在凹部（16.2 ... 16.3）的方向成角度，并且其被布置在上游 在主流动方向上的凹槽（16.2 ... 16.3）中，用于使流体流动进入凹槽（16.2 ... 16.3）。 通过该结构，可以在凹部（16.2 ... 16.3）内感应流体涡流（26.2 ... 26.3），并且可以基本上位于凹部（16.2 ... 16.3）内。

公开(公告)号：US20120223190A1

公开(公告)日：2012-09-06

申请号：US13410365

申请日：2012-03-02

申请人： Ulrich RIST ,  Andreas KNOLL

发明人： Ulrich RIST ,  Andreas KNOLL

IPC分类号： B64C21/04 ,  F01D5/14 ,  B64C21/06

CPC分类号： B64C21/025 ,  B64C21/08 ,  B64C2230/08 ,  B64C2230/18 ,  B64C2230/24 ,  Y02T50/166

摘要： An aerodynamic body with an aerodynamic body surface that creates a contoured surface for a fluid to stream around, with a device to influence the flow of the fluid streaming around the aerodynamic surface. The flow-influencing device includes a passage to link the fluid streaming around the aerodynamic surface with an actuator space of an aspirating and purging device situated in the aerodynamic body, and an indentation that is situated next to the passage, which is formed by a recessed section of the aerodynamic surface on a flow-influencing region within the contoured surface of the aerodynamic surface, so that a boundary wall is configured as part of the recessed surface lying opposite the indentation. The aspirating and purging device can generate a swirl in the flow of the fluid streaming around the aerodynamic surface, the rotational axis of which is directed along the assumed aerodynamic body chord direction.

摘要翻译： 具有空气动力学体表面的空气动力体，其产生用于流体流动的轮廓表面，具有影响流体围绕空气动力学表面流动的流体的装置。 流动影响装置包括将流体围绕空气动力学表面流动的流体连接到位于空气动力体中的抽吸和清洗装置的致动器空间的通道，以及位于通道旁边的凹陷，该凹陷由凹陷形成 在空气动力学表面的轮廓表面内的流动影响区域上的空气动力学表面的截面，使得边界壁被构造成与凹陷相对的凹陷表面的一部分。 抽吸和清洗装置可以在围绕空气动力学表面流动的流体流中产生涡流，该空气动力学表面的旋转轴沿着假定的空气动力学主体方向指向。

公开(公告)号：US20020190164A1

公开(公告)日：2002-12-19

申请号：US10170225

申请日：2002-06-12

发明人： Eric Loth ,  Philippe H. Geubelle ,  Scott R. White ,  Andrew G. Alleyne ,  Stephen T. Mcllwain ,  J. Craig Dutton ,  Daniel Tortorelli ,  David Davis

IPC分类号： B64C021/00

CPC分类号： B64C23/04 ,  B64C21/025 ,  B64C2230/06 ,  B64C2230/08 ,  B64C2230/20 ,  B64C2230/22 ,  B64C2230/24 ,  Y02T50/166

摘要： 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.

摘要翻译： 用于控制由结构的表面上的超音速冲击产生的冲击/边界层相互作用的装置包括在该结构中形成并在表面上具有开口的空腔。 板被附着到表面并覆盖开口。 多个襟翼形成在板上，并且可操作以响应于襟翼上的亚音速气流条件协同地关闭开口，并且打开开口以响应于襟翼上的超音速气流条件而允许气流通过空腔。

公开(公告)号：US06176454B1

公开(公告)日：2001-01-23

申请号：US09133858

申请日：1998-08-13

申请人： Fritz-Reinhard Grosche ,  Viktor Bader

发明人： Fritz-Reinhard Grosche ,  Viktor Bader

IPC分类号： B64C2104

CPC分类号： B64C21/025 ,  B64C23/04 ,  B64C2230/08 ,  B64C2230/20 ,  B64C2230/24 ,  B64C2230/28 ,  Y02T50/166

摘要： An apparatus serves for influencing the separation of a flow 2 from a body 1 immersed in the flow. The apparatus excites a shear layer 11 of the flow 2 at the immersed body 1 by periodic blowing and suction in order to act against further separation of the shear layer 11 from the immersed body 1. For this purpose, the apparatus has at least one passive cavity resistor 46, the hollow cylinder 4 of which has at least one opening 6 leading to the surface 10 of the body 1. The cavity resonator 46 is excited by the flow 2 thus creating compressional vibrations, and the compressional vibrations of the cavity resonator 46 excite the shear layer 11.

摘要翻译： 一种装置用于影响流动体2与浸入流体中的体1的分离。 该装置通过周期性的吹动和抽吸来激发流体2的剪切层11，以防止剪切层11与浸没的主体1进一步分离。为此目的，该装置具有至少一个被动 空腔电阻器46具有通向主体1的表面10的至少一个开口6.空腔谐振器46被流动2激发，从而产生压缩振动，并且空腔谐振器46的压缩振动 激发剪切层11。