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31. 发明授权

US09611807B2 Gas ejection cone for aircraft turbojet engines 有权
公开(公告)号：US09611807B2
公开(公告)日：2017-04-04
申请号：US14484684
申请日：2014-09-12
申请人： AIRCELLE
发明人： Pascal-Marie Paul Marcel Soulier , Jean-Bernard Guillon , Jean-Pierre Guegou
IPC分类号： F02K1/36 , F02K1/04 , B64C7/02
CPC分类号： F02K1/36 , B64C7/02 , F02K1/04
摘要： A gas ejection cone includes a cylindrical-shaped front cone portion, a conical-shaped rear cone portion, a ventilation tube and a support bearing of this drainage and/or ventilation tube. The ventilation tube extends inside the cylindrical-shaped front and conical-shaped rear cone portions and emerges at the end of the conical-shaped rear cone portion. In particular, the conical-shaped rear cone portion includes a front sub-portion connected to the cylindrical-shaped front cone portion, and a rear sub-portion removably secured to the front sub-portion. The rear sub-portion is further equipped with an outlet port of the ventilation tube.

32. 发明授权

US09505499B2 Methods and apparatus for supporting engines and nacelles relative to aircraft wings 有权
标题翻译：相对于飞机机翼来支持发动机和发动机舱的方法和装置
公开(公告)号：US09505499B2
公开(公告)日：2016-11-29
申请号：US14928953
申请日：2015-10-30
申请人： The Boeing Company
发明人： Jack W. Mauldin , David W. Kwok , John A. Weidler , Antonio B. Gonzales , Edward L. Lawson , Andrew C. Kulak
IPC分类号： B64D27/00 , B64D27/26 , B64D29/00 , B64C7/02 , B64D29/02 , B64F5/00
CPC分类号： B64D27/26 , B64C7/02 , B64D29/00 , B64D29/02 , B64D2027/262 , B64F5/10 , Y02T50/44
摘要： Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.
摘要翻译：公开了相对于飞机机翼来支撑发动机和机舱的方法和装置。示例性装置包括机舱; 第一支撑结构，沿着发动机的推力轴联接在所述机舱和所述机舱的第一侧之间; 第二支撑结构，其沿所述推力轴线联接在所述机翼和所述机舱的第二侧之间，所述第一支撑结构与所述机翼上的所述第二支撑结构间隔开，纵向平面延伸穿过所述第一支撑结构，所述第二支撑结构和所述推力轴线，所述第一支撑结构相对于所述机翼刚性地固定，以基本上防止所述第一支撑结构发动机的运动，所述第二支撑结构相对于所述机翼刚性地固定，以基本上防止所述发动机的运动通过第二支撑结构，第一和第二支撑结构将联接到发动机的相对侧，以使得推力载荷能够通过第一和第二支撑结构反作用于机翼。

33. 发明授权

US09469409B2 Aerodynamic fairing divided into sub-portions 有权
标题翻译：气动整流罩分为子部分
公开(公告)号：US09469409B2
公开(公告)日：2016-10-18
申请号：US14501910
申请日：2014-09-30
申请人： Airbus Operations (SAS)
发明人： Francois Peyruseigt , Thierry Gaches , Mathieu Kaleta , Nicolas Voyer , Delphine Chamaillard
IPC分类号： B64D29/06 , B64D29/00 , B64C1/00 , B64D27/26 , B64D29/02 , B64C7/02
CPC分类号： B64D29/00 , B64C1/0009 , B64C7/02 , B64D27/26 , B64D29/02 , B64D29/06
摘要： An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.
摘要翻译：包括至少一个子组件的空气动力整流罩，每个子组件具有相对于整流罩的纵向轴线横向定向的框架和设置有内表面的底板部分，底板部分固定到框架。整流罩进一步包括侧板，其固定到框架上，并且每个侧板基本上沿着整流罩的纵向轴线在整流罩的一侧和对称平面的另一侧延伸。子组件的地板部分不通过刚性连接机械连接。将地板划分成分离的部分允许在涡轮反应器的主要热流的作用下由地板膨胀施加的纵向热机械应力的减小。

34. 发明授权

US09452841B2 System and method for cooling an aircraft wing 有权
标题翻译：用于冷却飞机机翼的系统和方法
公开(公告)号：US09452841B2
公开(公告)日：2016-09-27
申请号：US14360925
申请日：2011-11-29
申请人： John Richardson
发明人： John Richardson
IPC分类号： B64D29/02 , B64D15/04 , B64D13/00 , B64C7/02 , B64D33/02
CPC分类号： B64D13/006 , B64C7/02 , B64D15/04 , B64D29/02 , B64D2033/0233
摘要： An aircraft comprises a turbine engine suspended from a wing by means of a pylon. Compressed hot air is bled off from the turbine engine. A bleed air duct in the wing conveys the compressed hot air towards a fuselage. In order to prevent overheating of aircraft parts that are relatively close to the bleed air duct, the following solution is proposed. The pylon comprises an opening with a covering structure projecting into a bypass exhaust flow from the turbine engine. The covering structure leaves a slit facing away from the bypass exhaust flow. An airflow path extends from openings in the wing to the slit left by the covering structure.
摘要翻译：一架飞机包括一个通过一个塔架从机翼悬挂的涡轮发动机。压缩的热空气从涡轮发动机排出。翼中的排风管将压缩的热空气传送到机身。为了防止相对靠近排气管道的飞机部件过热，提出了以下解决方案。塔架包括具有从涡轮发动机突出到旁路排气流中的覆盖结构的开口。覆盖结构使得切口背离旁路排气流。气流路径从机翼中的开口延伸到被覆盖结构留下的缝隙中。

35. 发明申请

US20160107746A1 PERFORATED SURFACE FOR SUCTION-TYPE LAMINAR FLOW CONTROL 有权
标题翻译：吸入式层压流量控制的表面
公开(公告)号：US20160107746A1
公开(公告)日：2016-04-21
申请号：US14516200
申请日：2014-10-16
申请人： Rohr, Inc.
发明人： Sean Tiwari , Luby Weaver
IPC分类号： B64C21/06 , B64C7/02 , B23K26/382 , B32B3/26 , B32B15/08
CPC分类号： B64C21/06 , B23K26/382 , B32B3/266 , B32B15/08 , B32B2262/00 , B32B2571/00 , B32B2605/18 , B64C7/02 , B64D2033/0226 , F15D1/008 , F15D1/12 , Y02T50/166
摘要： An apparatus is provided for promoting laminar flow. The apparatus includes a panel extending between an interior surface and an exterior air flow surface. The panel includes a plurality of macro apertures and a plurality of micro apertures. A first one of the macro apertures extends into the panel from the interior surface. A first one of the micro apertures extends into the panel from the exterior air flow surface and is fluidly coupled with the first one of the macro apertures.
摘要翻译：提供了用于促进层流的装置。该装置包括在内表面和外部空气流动表面之间延伸的面板。面板包括多个微孔和多个微孔。宏孔中的第一个从内表面延伸到面板中。微孔中的第一个从外部空气流动表面延伸到面板中并与第一个宏观孔径流体连接。

36. 发明申请

US20120261521A1 NACELLE INCORPORATING AN ELEMENT FOR CONNECTING A LIP AND AN ACOUSTIC ATTENUATION PANEL TOGETHER 有权
标题翻译：连接一个LIP和一个声音衰减面板的元件的NACELLE
公开(公告)号：US20120261521A1
公开(公告)日：2012-10-18
申请号：US13518041
申请日：2010-12-21
申请人： Alain Porte , Jacques Lalane
发明人： Alain Porte , Jacques Lalane
IPC分类号： B64C7/02
CPC分类号： B64D33/02 , B64C7/02 , B64D29/00 , B64D29/06 , B64D2033/0206
摘要： An aircraft nacelle includes a first subassembly consisting of a pipe (112) channeling an airflow in the direction of an engine having a covering or panel (118) for acoustic treatment, including, from the inside to the outside, a reflecting layer (120), at least one cellular structure (122), and at least one acoustically resistive structure (124) forming the aerodynamic surface of the pipe (112), as well as a second subassembly consisting of a lip (116) and a front frame (126), characterized in that it includes at least one connection element (134) which is separate from the two subassemblies and connected to a portion of the pipe (112) and to a portion of the lip forming an extension of the portion of the pipe at different points so as to be capable of enabling a relative movement between the two subassemblies.
摘要翻译：一种飞机机舱包括一个第一子组件，该组件包括一个管道（112），该管道（112）引导具有用于声学处理的覆盖物或面板（118）的发动机的方向上的气流，包括从内到外的反射层（120），至少一个蜂窝结构（122）和形成管（112）的空气动力学表面的至少一个声阻结构（124），以及由唇部（116）和前框架（126）组成的第二子组件），其特征在于，其包括至少一个连接元件（134），其与两个子组件分离并连接到管道（112）的一部分，并且与唇部的一部分形成管的该部分的延伸部分以便能够实现两个子组件之间的相对移动。

37. 发明申请

US20090289149A1 Engine pod for an aircraft with a vortex generator arrangement 有权
标题翻译：用于具有涡流发生器装置的飞机的发动机舱
公开(公告)号：US20090289149A1
公开(公告)日：2009-11-26
申请号：US12454922
申请日：2009-05-26
申请人： Detlev Schwetzler
发明人： Detlev Schwetzler
IPC分类号： B64C23/06 , B64C7/02
CPC分类号： B64C23/06 , B64C7/02 , B64D29/02 , Y02T50/162
摘要： The invention pertains to an engine pod for an aircraft, one side of which features several fin-shaped vortex generators (3, 4, 5) such that the overall vorticity field generated by the vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases in order to improve the maximum lift, wherein the first vortex generator lies within a positioning corridor (K31) that is situated between two boundary lines (51, 52), wherein the point of origin (51a) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and the longitudinal engine pod coordinate X=L/4, the end point (51b) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=25 degrees and the longitudinal engine pod coordinate X=L·⅔, the point of origin (52a) of the second boundary line (52) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=90 degrees and the longitudinal engine pod coordinate X=L/4 and the end point (52b) of the second boundary line (52) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=55 degrees and the longitudinal engine pod coordinate X=L·⅔.
摘要翻译：本发明涉及一种用于飞行器的发动机舱，其一侧具有若干鳍形涡流发生器（3,4,5），使得由涡流发生器产生的整体涡流场在翼展方向上延伸超过增加的翼型面积随着迎角增加以改善最大升力，其中第一涡流发生器位于位于两个边界线（51,52）之间的定位走廊（K31）内，其中，该起点（51a）第一边界线（51）是发动机舱的圆周上的点，圆周发动机舱角度phi = 35度，纵向发动机舱架坐标X = L / 4，第一边界线的端点（51b） 51）是发动机舱的圆周上的点，圆周发动机舱角度为phi = 25度，纵向发动机舱座标X = L.2 / 3，第二边界线（52）的起点（52a））是圆环上的点 e，发动机舱的周向发动机舱角度为phi = 90度，纵向发动机舱架坐标X = L / 4，第二边界线（52）的端点（52b）为发动机圆周上的点圆周发动机舱角度phi = 55度，纵向发动机舱架坐标X = L.2 / 3。

38. 发明授权

US06978971B1 Methods and apparatuses for controlling airflow proximate to engine/airfoil systems 有权
标题翻译：用于控制靠近发动机/翼型系统的气流的方法和装置
公开(公告)号：US06978971B1
公开(公告)日：2005-12-27
申请号：US10868238
申请日：2004-06-15
申请人： Roy Dun
发明人： Roy Dun
IPC分类号： B64C7/02 , B64C9/24 , B64C29/00 , B64D27/18 , B34C9/24
CPC分类号： B64D27/18 , B64C7/02 , B64C9/24 , Y02T50/32
摘要： Methods and apparatuses for controlling airflow proximate to engine/airfoil systems are disclosed. In one embodiment, an aircraft system includes an airfoil and an engine unit at least proximate to the airfoil with a gap between a portion of the airfoil and a portion of the engine unit. The system can further include a flow control device proximate to the gap and positionable among at least three stationary positions, including a retracted position in which the gap has a first area through which fluid can flow, a first extended position in which the gap is at least approximately aerodynamically sealed, and a second extended position in which the gap has a second smaller area through which fluid can flow. A control system can be coupled to the flow control device to move the flow control device among these positions.
摘要翻译：公开了用于控制靠近发动机/翼型系统的气流的方法和装置。在一个实施例中，飞行器系统包括至少靠近机翼的翼型件和发动机单元，翼型件的一部分与发动机单元的一部分之间具有间隙。所述系统还可以包括靠近所述间隙的流量控制装置，并且可在至少三个静止位置之间定位，包括缩回位置，在该缩回位置，所述间隙具有流体可以流过的第一区域，所述间隙处于所述第一延伸位置至少近似空气动力学密封，以及第二延伸位置，其中所述间隙具有流体可以流过的第二较小区域。控制系统可以耦合到流量控制装置以在这些位置之间移动流量控制装置。

39. 发明授权

US06866223B2 Process for forming a sector of an air intake lip, device for practicing the same, and sector thus obtained 有权
标题翻译：用于形成进气口的扇区的过程，用于实施该进气口的装置和由此获得的扇区
公开(公告)号：US06866223B2
公开(公告)日：2005-03-15
申请号：US10390908
申请日：2003-03-19
申请人： Lucien Chevalier
发明人： Lucien Chevalier
IPC分类号： B21C23/12 , B21C37/28 , B64C7/02
CPC分类号： B21C37/28 , B21C23/12 , B29C65/08 , B29C66/45 , B29C66/69 , B29C66/836
摘要： The object of the invention is a process for forming sectors of the air intake lip of an aircraft nacelle, of U-shaped cross-section, characterized in that it comprises producing, from a cylindrical billet (11) of a suitable material, by hot die pressing, a tubular profile (12) of U-shaped cross-section whose ends are interconnected, a portion of the section formed by the U having a development less by several percent than the development of the smallest cross-section of the lip sector to be obtained, in giving to the profile (12) at the outlet of the die (15) a curvature whose radius is substantially equal to the mean radius of said sector, then in forming and calibrating the profile (12) to the final shapes of the sector by hydraulic expansion in a matrix whose interior corresponds to the external volume of said sector increased by the resilient return of the material to be expanded, and finally, cutting off the tubular product thus formed to separate the portion of U-shaped cross-section constituting said lip sector.
摘要翻译：本发明的目的是一种用于形成U形横截面的飞机机舱的进气口的扇区的方法，其特征在于，其包括通过热的方式从适当材料的圆柱形坯料（11）模压，U形横截面的管状轮廓（12）的端部相互连接，由U形成的部分的部分的开发比唇部部分的最小横截面的发展少几百倍要获得的是，在模具（15）出口处的轮廓（12）上，其曲率半径基本上等于所述扇区的平均半径，然后在将轮廓（12）形成和校准到最终形状通过液体膨胀在其内部对应于所述扇区的外部体积的基体中的液压膨胀通过待膨胀的材料的弹性返回而增加，并且最后切断由此形成的管状产品以将U形横截面 -se 表示唇部部分。

40. 发明授权

US5609313A Aircraft propulsive power unit 失效
标题翻译：飞机推进动力装置
公开(公告)号：US5609313A
公开(公告)日：1997-03-11
申请号：US307722
申请日：1994-10-24
申请人： Derek Cole , Philip D. Sherry , Alan J. Blair
发明人： Derek Cole , Philip D. Sherry , Alan J. Blair
IPC分类号： B64C7/02 , B64D29/00 , B64D29/06
CPC分类号： B64D29/08 , B64D29/00
摘要： An aircraft propulsive power unit (19) comprises a nacelle structure (20) housing an engine and having a forward nacelle portion (21) and a rearward nacelle portion (131). The rearward end of the forward nacelle portion (21) in an operational position adjoins the forward end of the rearward nacelle portion (131) and the forward end of the forward nacelle portion (21) includes an intake opening leading to an intake barrel (28) upstream of the engine for the supply of intake air to the engine. The forward nacelle portion (21) has an uninterrupted or substantially uninterrupted low drag exterior surface thereover and the power unit includes support structure to support the forward nacelle portion (21) while permitting it to be moved forwardly on the support structure from the operational position to a forward position in which it is supported by the support structure forwardly of the operational position to provide access to components of the power unit (19) which are inaccessible with the forward nacelle portion (21) in the operational position.
摘要翻译： PCT No.PCT / GB94 / 00131 Sec。 371日期：1994年10月24日 102（e）日期1994年10月24日PCT 1994年1月24日PCT PCT。第WO94 / 16945号公报日期1994年8月4日飞机推进动力单元（19）包括容纳发动机并具有前部机舱部分（21）和后部机舱部分（131）的机舱结构（20）。前部机舱部分（21）的后端处于操作位置，邻接后部机舱部分（131）的前端，并且前部机舱部分（21）的前端包括通向进气筒（28）的进气口），用于向发动机供应进气。前部机舱部分（21）在其上方具有不间断或基本上不间断的低阻力外表面，并且动力单元包括支撑结构以支撑前部机舱部分（21），同时允许其在支撑结构上从操作位置向前移动到前部位置，其中由支撑结构向前支撑在操作位置，以提供进入动力单元（19）的部件，这些部件在前部机舱部分（21）处于操作位置时是不可接近的。

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