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。

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'）。

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。

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 。

公开(公告)号：US09261021B2

公开(公告)日：2016-02-16

申请号：US12307886

申请日：2007-07-04

申请人： Alain Porte ,  Fabrice Gantie ,  Frederic Chelin ,  Patrick Oberle

发明人： Alain Porte ,  Fabrice Gantie ,  Frederic Chelin ,  Patrick Oberle

IPC分类号： F02B27/00 ,  F02C7/04 ,  F02K3/06

CPC分类号： F02C7/04 ,  F02K3/06 ,  F05D2240/14 ,  F05D2300/603 ,  Y02T50/672 ,  Y10T137/0536

摘要： An internal wall of an air intake and a housing of a fan form a single tubular piece made from a fiber/resin composite material. A rear end has the single tubular component connected by a flange and bolts to an external cowl of the fan duct, such that the rear end of the tubular component is uniform and the flange is attached and fixed to the rear end.

摘要翻译： 空气入口的内壁和风扇的壳体形成由纤维/树脂复合材料制成的单个管状件。 后端具有通过法兰和螺栓连接到风扇管道的外部整流罩的单个管状部件，使得管状部件的后端是均匀的并且凸缘被附接并固定到后端。

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。

公开(公告)号：US08794572B2

公开(公告)日：2014-08-05

申请号：US13523282

申请日：2012-06-14

申请人： Alain Porte ,  Frederic Chelin

发明人： Alain Porte ,  Frederic Chelin

IPC分类号： B64D15/12

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  B64D2033/0286

摘要： An air intake of an aircraft nacelle includes:on the one hand, a lip (42) that is defined by a wall (52) whose surface that is in contact with the aerodynamic flows is extended on the inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant and on the outside of the nacelle by an outside wall (46), and, on the other hand, a surface-type Joule-effect defrosting system (58); at least a first alveolar structure (60.1) that is made of a material that conducts the heat and that is flattened against the inside surface of the wall (52) and inserted between the wall (52) and the defrosting system (58), and at least one second alveolar structure (60.2) that is made of composite material that is adjacent to the first structure (60.1).

摘要翻译： 飞机机舱的进气口包括：一方面是由壁（52）限定的唇缘（42），其表面与空气动力学流动接触，其通过内壁延伸在机舱内部 （44），其与通过外壁（46）在发电厂和机舱外部排空的管道相接触，另一方面是表面型焦耳效应除霜系统（58）; 至少第一肺泡结构（60.1），其由传导热量的材料制成并且被平坦化抵靠壁（52）的内表面并插入在壁（52）和除霜系统（58）之间，以及 至少一个第二肺泡结构（60.2），其由与所述第一结构（60.1）相邻的复合材料制成。

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。

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。

公开(公告)号：US20130098471A1

公开(公告)日：2013-04-25

申请号：US13632820

申请日：2012-10-01

申请人： ALAIN PORTE ,  FRÉDÉRIC CHELIN ,  PASCAL GALLETTI

发明人： ALAIN PORTE ,  FRÉDÉRIC CHELIN ,  PASCAL GALLETTI

IPC分类号： F02C7/04

CPC分类号： F02C7/04 ,  B64D15/04 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  F02C7/047 ,  Y02T50/672 ,  Y10T137/0536

摘要： The object of the invention is an aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip annular channel within which hot air circulates, and a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and one reflective layer as well as ducts for channeling hot air, at least one conduit with opening which opens into annular channel being provided for carrying hot air up to the panel for acoustic treatment, wherein opening is used for channeling hot air in direction which forms an angle β of less than 60° with hot air flow direction into annular channel.

摘要翻译： 本发明的目的是一种飞机机舱，其包括由形成进气口的内部管道延伸的唇缘，与所述唇部环形通道限定的前部框架，热空气循环在该前部框架中，以及用于声学处理的面板， 声阻性层，至少一个蜂窝结构和一个反射层以及用于引导热空气的导管，至少一个具有开口的开口的管道，其设置有用于将热空气传送到面板进行声学处理，其中开口是 用于将热空气流动方向形成角度β小于60°的方向引导到环形通道中。