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31. 发明授权

US06479124B1 Composite material panel with shock-protected edges 有权
标题翻译：具有防震边缘的复合材料面板
公开(公告)号：US06479124B1
公开(公告)日：2002-11-12
申请号：US09341960
申请日：1999-08-10
申请人： Alain Porte , Robert Andre
发明人： Alain Porte , Robert Andre
IPC分类号： B32B1514
CPC分类号： B32B3/02 , B29C70/86 , B29C70/885 , B32B5/26 , B32B7/12 , B32B2260/021 , B32B2260/046 , B32B2262/103 , B32B2307/558 , B32B2307/714 , B32B2605/18 , B64C1/12 , B64D29/00 , Y02T50/43 , Y10T428/23 , Y10T428/238 , Y10T428/239 , Y10T428/2419 , Y10T428/24777 , Y10T428/24793
摘要： A panel of composite material, in particular with a thermosetting or thermoplastic matrix, with edges and/or external surface protected from shocks and erosion, for any streamlining element for housings or nacelles of aeronautical motors, comprises, over all or a portion of its edges, a cladding which forms a border overlapping the two opposite surfaces of the panel. The border comprises a metallic cloth connected to the structure of the panel by an adhesive agent, diffused through the cloth. The panel is particularly applicable to aircraft.
摘要翻译：特别是具有热固性或热塑性基体的面板，具有防止冲击和侵蚀的边缘和/或外部表面的复合材料面板，用于航空电动机的壳体或机舱的任何流线型元件包括在其全部或一部分边缘上，形成与面板的两个相对表面重叠的边界的包层。边框包括通过粘合剂连接到面板结构的金属布，通过布扩散。专门面板特别适用于飞机。

32. 发明授权

US06427434B2 Device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit 有权
标题翻译：用于排放喷气发动机进气罩的热空气的装置，具有除冰电路
公开(公告)号：US06427434B2
公开(公告)日：2002-08-06
申请号：US09739640
申请日：2000-12-20
申请人： Alain Porte , Stéphane Viala
发明人： Alain Porte , Stéphane Viala
IPC分类号： F02C7047
CPC分类号： B64D15/04 , B64D33/02 , B64D2033/0233 , F02C7/047 , Y02T50/672 , Y10T137/0536
摘要： A device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit. The air inlet cowl for a jet engine, the leading edge of which is hollow and swept with a flow of deicing hot air, includes orifices for discharging the hot air flow to the outside of the leading edge, which form an arrangement such that at least two pressurized hot air jets passing through two adjacent orifices have, downstream of a calibration piece in which the orifices are made, different inclinations with respect to the calibration piece.
摘要翻译：一种用于排出用于喷气发动机进气罩的热空气的装置，具有除冰电路。用于喷气发动机的空气入口罩，其前缘是中空的并且具有除冰热空气的流动，包括用于将热空气流排放到前缘的外部的孔，其形成至少这样的布置通过两个相邻孔口的两个加压的热空气喷嘴在其上形成有孔的校准件的下游具有相对于校准件的不同倾斜度。

33. 发明授权

US5722231A Turbofan with thrust reversal doors not submitted to bypass air in their inactive position 失效
标题翻译：涡轮风扇带反推式转向门不能绕过空气处于非活动状态
公开(公告)号：US5722231A
公开(公告)日：1998-03-03
申请号：US690165
申请日：1996-07-26
申请人： Alain Porte
发明人： Alain Porte
IPC分类号： F02K1/70 , F02K3/02
CPC分类号： F02K1/70
摘要： A turbofan, preferentially with separated-flows or short nacelle, comprises two thrust reversal doors normally housed in casings formed in the nacelle and located totally outside the inner enclosure of the nacelle. When a thrust reversal effect is sought, the doors are directed in the prolongation of the fan channel, behind the rear end of the nacelle. Thus, the doors are not submitted to the engine bypass air of the jet engine when the aircraft is in flight and the inner enclosure of the nacelle presents neither leak nor discontinuity and may be totally anti-noise treated.
摘要翻译：涡轮风扇，优选具有分离的流动或短的机舱，包括通常容纳在形成在机舱中并且完全位于机舱的内部外壳之外的壳体中的两个推力反转门。当要求推力反转效果时，门被引导到风机通道的延长部分，在机舱的后端后面。因此，当飞行器处于飞行状态时，门不会被送到喷气发动机的发动机旁路空气，并且机舱的内部壳体既不泄漏也不显示不连续性，并且可以进行完全抗噪声处理。

34. 发明授权

US5642615A Turbofan engine with a floating pod 失效
标题翻译： Turbofan发动机带有浮动荚
公开(公告)号：US5642615A
公开(公告)日：1997-07-01
申请号：US618840
申请日：1996-03-20
申请人： Alain Porte , Danilo Ciprian
发明人： Alain Porte , Danilo Ciprian
IPC分类号： B64D27/18 , F02K3/02
CPC分类号： B64D27/18
摘要： In a turbofan engine, the mechanical connection between the pod (12) and the fan stator case (10) is limited to a centering system (22) in the immediate vicinity of the arms (20) by which the fan stator case is mounted on the central portion (16) of the engine. The aerodynamic and inertia loads applied to the pod (12), particularly on take-off and landing, consequently only lead to an acceptable deformation of the fan stator case (10). Thus, the gap between said case and the fan (18) can be kept to a very small value, which ensures maximum engine efficiency. Moreover, the centering system (22) prevents an excessive radial displacement (J') between the front of the fan stator case (10) and the adjacent portion of the pod.
摘要翻译：在涡轮风扇发动机中，舱（12）和风扇定子箱（10）之间的机械连接被限制在靠近臂（20）的定心系统（22），风扇定子壳体通过该定心系统安装在发动机的中心部分（16）。施加到舱（12）上的空气动力学和惯性载荷，特别是在起飞和着陆时，仅导致风扇定子壳（10）可接受的变形。因此，所述壳体和风扇（18）之间的间隙可以保持在非常小的值，这确保了最大的发动机效率。此外，定心系统（22）防止风扇定子壳体（10）的前部和容器的相邻部分之间的过大的径向位移（J'）。

35. 发明授权

US5303508A Access door, especially for an aircraft engine cowling, provided with synchronized pivoting articulated flap 失效
标题翻译：检修门，特别适用于飞机发动机罩，配有同步旋转的铰接式挡板
公开(公告)号：US5303508A
公开(公告)日：1994-04-19
申请号：US842079
申请日：1992-02-26
申请人： Alain Porte
发明人： Alain Porte
IPC分类号： B64C1/14 , B64D29/08 , E05D3/06 , E05D15/26 , E05F17/00
CPC分类号： B64C1/1446 , B64D29/06 , E05D15/264 , E05D3/14 , E05Y2900/00 , E05Y2900/502
摘要： A device for tight closure of an opening in a wall including a panel which closes the opening partially and opens to one side of the opening by pivoting about a substantially fixed axis on the other side of the opening at a substantial distance therefrom. The panel is at least approximately aligned in the direction transverse to the wall with an edge of the opening. The panel closes the opening except for a gap parallel to the axis between the edge of the opening and an inside edge of the panel which is substantially parallel to the axis. A mobile flap closes the gap. It is pivoted to the panel about a second axis extending along the inside edge of the panel. At least one link is pivoted about a substantially fixed third axis on the same side of the opening as the first axis and about a fourth axis joined to the mobile flap.
摘要翻译：一种用于紧密封闭墙壁中的开口的装置，包括面板，所述面板通过围绕开口的另一侧上的基本上固定的轴线枢转而部分地封闭开口并且与开口的一侧敞开。面板至少大致对齐在横向于墙壁的方向上与开口的边缘。面板关闭开口，除了平行于开口的边缘和基本上平行于轴线的面板的内边缘之间的轴线的间隙。移动挡板封闭间隙。围绕围绕面板的内边缘延伸的第二轴线枢转到面板。至少一个连杆围绕与第一轴线在开口的同一侧上的基本上固定的第三轴线和围绕连接到移动挡板的第四轴线枢转。

36. 发明授权

US09422062B2 Air intake arrangement for a vehicle, in particular an aircraft 有权
标题翻译：车辆的进气装置，特别是飞机
公开(公告)号：US09422062B2
公开(公告)日：2016-08-23
申请号：US12597071
申请日：2008-04-14
申请人： Franck Alvarez , Emeric Chancerelle , Alain Porte , Damien Prat
发明人： Franck Alvarez , Emeric Chancerelle , Alain Porte , Damien Prat
IPC分类号： B64D33/02 , B64D33/08
CPC分类号： B64D33/08 , B64D33/02 , B64D2033/0286
摘要： Disclosed is an air intake arrangement for an aircraft. The arrangement includes an air intake orifice, which is configured to bleed off a flow of external air, pass the external air through at least one air passage channel and ventilate a confined zone of the aircraft. An aerodynamically controlled shut-off means, comprised of a controllable mobile element and control means, is configured to regulate flow of the external air through the air passage channel to vary a cross section of the air passage channel relative to aircraft speed. The control means are arranged in the air passage channel and include an aerodynamic surface configured to apply a lift force to the control means to vary the cross section of the air passage channel as the flow of external air passes through the channel and toward the confined zone.
摘要翻译：公开了一种用于飞机的进气装置。该装置包括进气孔，其构造成排出外部空气流，使外部空气通过至少一个空气通道通道并使飞行器的限制区域通风。由可控制的移动元件和控制装置组成的空气动力学控制的关闭装置构造成调节外部空气通过空气通道通道的流动，以相对于飞行器速度改变空气通道通道的横截面。控制装置布置在空气通道通道中，并且包括空气动力学表面，其构造成当外部空气流通过通道并朝向限制区域时，向控制装置施加提升力以改变空气通道通道的横截面。

37. 发明授权

US08960589B2 Panel for an air intake of an aircraft nacelle that ensures optimized acoustic treatment and frost treatment 有权
标题翻译：用于飞机机舱进气口的面板，确保优化的声学处理和霜冻处理
公开(公告)号：US08960589B2
公开(公告)日：2015-02-24
申请号：US12968562
申请日：2010-12-15
申请人： Alain Porte , Frédéric Chelin , Stéphane Dida , Arnaud Hormiere
发明人： Alain Porte , Frédéric Chelin , Stéphane Dida , Arnaud Hormiere
IPC分类号： B64C23/00 , B64D15/04 , B64D33/02 , F02C7/045 , F02C7/047
CPC分类号： B64D15/04 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/047 , F05D2260/962 , Y02T50/672
摘要： An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer (50) between which are arranged at least one alveolar structure (52) with a number of cells dedicated to the acoustic treatment, and de-icing cavities (58) in which hot air circulates in contact with the acoustically resistive layer to ensure a frost treatment, characterized in that it includes holes for supplying de-icing cavities (58) with hot air and in that the capacity to treat the frost is adjusted along the zones by modifying the open surface ratio that results from the holes.
摘要翻译：声学处理面板包括限定与空气动力学流接触的飞行器表面的声阻层，反射层（50）之间布置有至少一个肺泡结构（52），多个细胞专用于声学处理和除冰空腔（58），其中热空气与声阻层接触以循环，以确保霜冻处理，其特征在于，其包括用于向热空气供应除冰空腔（58）的孔通过改变由孔产生的开放表面比例，沿着区域调节处理霜的能力。

38. 发明授权

US08757546B2 Device for shrouding an aircraft nacelle 有权
标题翻译：用于遮蔽飞机机舱的装置
公开(公告)号：US08757546B2
公开(公告)日：2014-06-24
申请号：US13054290
申请日：2009-07-15
申请人： Alain Porte , Robert Andre , Matthieu Fargues
发明人： Alain Porte , Robert Andre , Matthieu Fargues
IPC分类号： B64C1/14
CPC分类号： B64D29/06
摘要： An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for encircling it in the form of at least one flexible element (38), guide elements (40) for allowing the at least one flexible element (38) to follow the curved profile of the at least one door, a first anchoring point (42) of the at least one flexible element (38) integral with a first edge (78) of the cap and another anchoring point of the at least one flexible element (38) integral with a second edge (80) of the cap, whereby the anchoring points (42) allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap (14) and the at least one door (16).
摘要翻译：飞机机舱包括进气口（12），其后面是与被称为盖子的桅杆成一体的部分（14），以及至少一个具有弯曲轮廓的门（16）的一部分（14），以及用于将其包围的装置至少一个柔性元件（38）的形式，用于允许所述至少一个柔性元件（38）跟随所述至少一个门的弯曲轮廓的导向元件（40），所述至少一个门的第一锚定点（42）至少一个柔性元件（38）与所述盖的第一边缘（78）成一体并且所述至少一个柔性元件（38）的另一个固定点与所述盖的第二边缘（80）成一体，由此所述锚定点允许在平行于机舱的纵向轴线的方向上在盖（14）和至少一个门（16）之间的相对平移运动。

39. 发明授权

US08646723B2 Device for connecting an air inlet with an aircraft nacelle actuator assembly 有权
标题翻译：用于将进气口与飞机机舱致动器组件连接的装置
公开(公告)号：US08646723B2
公开(公告)日：2014-02-11
申请号：US13120025
申请日：2009-09-17
申请人： Alain Porte , Matthieu Fargues , Jacques Lalane
发明人： Alain Porte , Matthieu Fargues , Jacques Lalane
IPC分类号： B64D29/00
CPC分类号： B64D33/02 , B64D29/06 , B64D2033/0206 , B64D2033/0286 , F01D25/243 , F02C7/045
摘要： An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.
摘要翻译：飞机机舱包括进气口，其使得可以沿着布置在管道的延伸部中的发电厂的管道的方向在管道中引导空气，由此进气口的管道包括至少一个面板其将声学处理与与进入机舱的空气动力流接触的声阻性多孔层，至少一个肺泡结构以及形成面板后表面的反射或不可渗透层，确保进气口和发电厂之间的连接包括至少一个通过多个连接元件连接到进气口的机翼，其特征在于，一些连接元件具有与面板边缘相切的轴线，进气管道。

40. 发明授权

US08308110B2 System for defrosting the leading edge sheath of an air inlet hood for a turboengine 有权
标题翻译：用于对涡轮发动机的进气罩的前缘护套进行除霜的系统
公开(公告)号：US08308110B2
公开(公告)日：2012-11-13
申请号：US11993009
申请日：2006-06-15
申请人： Alain Porte
发明人： Alain Porte
IPC分类号： B64D15/02
CPC分类号： F02C7/047 , B64D2033/0206 , B64D2033/0233 , F02C7/28 , Y02T50/672
摘要： The system for defrosting the leading edge sheath of an air intake hood for a turboengine comprises a hot pressure air supply duct (60) and a protective shell (90) which are longitudinally rigid and rigidly fixed to the partition (5) of a caisson (10), wherein said protective shell (90) is slidable with respect to a sliding bearing (15) embodied in the partition (11) and said air supply duct (60) is connected to the protective shell (90) by an elastic wall (16) closing an insulating space (12) and enabling relative longitudinal movements to be carried out between the air supply duct (60) and the protective shell (90).
摘要翻译：用于涡轮发动机的进气罩的前缘护套的除霜系统包括热压空气供应管道（60）和保护壳体（90），其被纵向刚性并且刚性地固定到沉箱（5） 10），其中所述保护壳（90）可相对于在隔板（11）中实施的滑动轴承（15）滑动，并且所述空气供应管道（60）通过弹性壁连接到保护壳（90） 16）关闭绝缘空间（12）并且能够在空气供应管道（60）和保护壳体（90）之间执行相对的纵向运动。

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