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：US20110168839A1

公开(公告)日：2011-07-14

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： F02C7/045 ,  B64D33/02

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：US07971684B2

公开(公告)日：2011-07-05

申请号：US12528017

申请日：2008-02-19

申请人： Fabrice Gantie ,  Bernard Duprieu ,  Valerie Frustie ,  Alain Porte ,  Thomas Gilles ,  Jacques Lalane

发明人： Fabrice Gantie ,  Bernard Duprieu ,  Valerie Frustie ,  Alain Porte ,  Thomas Gilles ,  Jacques Lalane

IPC分类号： E04B1/82

CPC分类号： G10K11/172 ,  F02C7/24 ,  F02K1/827 ,  G10K11/168

摘要： A panel for acoustic treatment connected to a surface of an aircraft, includes—from the outside to the inside—an acoustically resistive porous layer, at least one alveolar structure, and a reflective or impermeable layer, whereby the acoustically resistive porous layer includes—at the outside surface that can be in contact with the aerodynamic flows—one sheet or piece of sheet metal including open zones (14) that allow sound waves to pass and filled zones (16) that do not allow sound waves to pass, characterized in that the sheet or piece of sheet metal of the acoustically resistive layer includes sets of microperforations (18), whereby each set of microperforations forms an open zone (14), the sets of microperforations being separated from one another by at least one series of bands separated by filled zones (16).

摘要翻译： 连接到飞行器表面的用于声学处理的面板包括从外部到内部的声阻多孔层，至少一个肺泡结构以及反射或不可渗透层，其中所述声阻多孔层包括 可以与气动流动接触的外表面 - 包括允许声波通过并且不允许声波通过的区域（16）的开放区域（14）的一片或片状金属片，其特征在于， 阻声层的片状物或片状物包括一组微穿孔（18），由此每组微穿孔形成开放区域（14），所述微穿孔组彼此分开至少一系列带分离 通过填充区（16）。

公开(公告)号：US20100276548A1

公开(公告)日：2010-11-04

申请号：US12809742

申请日：2008-12-16

申请人： Alain Porte ,  Jacques Lalane ,  Fabrice Gantie ,  Jacques Barillot-Creuzet

发明人： Alain Porte ,  Jacques Lalane ,  Fabrice Gantie ,  Jacques Barillot-Creuzet

IPC分类号： B64D33/02

CPC分类号： B64D33/02 ,  B64D15/04 ,  B64D2033/0206 ,  B64D2033/0233

摘要： An acoustic treatment structure related to a leading edge onto which an aerodynamic stream flows, in particular at an air intake of an aircraft nacelle, includes—from the outside to the inside—at least one acoustically resistive substructure (30), at least one alveolar substructure including strips (32) of cells, arranged in a direction that is essentially perpendicular to the direction of flow of the aerodynamic stream, and at least one reflective layer (34). Each strip (32) includes a first part that insulates the strips from one another, called a support, with a U-shaped cross-section in the longitudinal direction, whose open surface that is opposite to the bottom of the U shape is flattened against the acoustically resistive substructure (30), and at least a second part, called partitioning, making it possible to partition the space that is delimited by the support and the acoustically resistive substructure (30) into cells.

摘要翻译： 与空气动力流流动的前缘相关联的声学处理结构，特别是在飞机机舱的空气入口处，包括 - 从外部至内部至少一个声阻子结构（30），至少一个肺泡 子结构，包括沿基本上垂直于空气动力流的流动方向布置的细胞条带（32），以及至少一个反射层（34）。 每个条带（32）包括第一部分，其将条带彼此绝缘，称为支撑件，其在纵向方向上具有U形横截面，其与U形底部相对的开口表面被平坦化 声阻抗子结构（30）和至少第二部分（称为分割），使得可以将由支撑体和声阻子结构（30）限定的空间分隔成单元。

公开(公告)号：US20120048389A1

公开(公告)日：2012-03-01

申请号：US13145451

申请日：2010-01-28

申请人： Frédéric Chelin ,  Alain Porte ,  Fabrice Gantie ,  Jacques Lalane

发明人： Frédéric Chelin ,  Alain Porte ,  Fabrice Gantie ,  Jacques Lalane

IPC分类号： F02K99/00

CPC分类号： B64D15/04 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  Y02T50/67 ,  Y02T50/672 ,  Y10T137/0536

摘要： An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.

摘要翻译： 包括管（32），周壁（34），唇缘（36）和连接周壁（34）和管（32）并且与唇缘（36）形成的前框架（38）的飞机机舱 ）具有用于霜冻处理的热空气可以循环的空间（50），其中包括用于复合材料声学处理的涂层（44）的管（32）的特征在于，所述机舱包括至少一个元件 （52），其由插入在所述唇部（36）和所述管（32）之间的导热材料制成，以确保所述唇部（36）和所述管（32）的空气动力学表面的连续性和来自所述空间 （50）朝向所述机舱的后部，由此所述至少一个元件（52）包括由耐热材料制成的用于声学处理的涂层（54）。

公开(公告)号：US09352844B2

公开(公告)日：2016-05-31

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： B64D29/00 ,  B64D33/02 ,  B64D29/06 ,  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。

公开(公告)号：US08684301B2

公开(公告)日：2014-04-01

申请号：US12990562

申请日：2009-04-28

申请人： Alain Porte ,  Jacques Lalane

发明人： Alain Porte ,  Jacques Lalane

IPC分类号： B64D33/02

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  F02C7/045 ,  Y02T50/671

摘要： An aircraft nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel.

摘要翻译： 飞机机舱包括波衰减面板，其限制或防止在发电厂泵送期间产生的至少一个波的传播，并且包括与允许至少一个波通过的空气流接触的层， 至少一个肺泡结构以及反射或不渗透层，其中所述波衰减面板插入在所述进气口和所述发电厂之间，并且与所述气流接触的所述层确保所布置的空气动力学表面的连续性 下游和上游，并且波浪衰减面板包括可以插入进气口和发电厂之间的插入件，以便不粉碎波浪衰减面板。

公开(公告)号：US08567712B2

公开(公告)日：2013-10-29

申请号：US13008592

申请日：2011-01-18

申请人： Alain Porte ,  Jacques Lalane ,  Franck Alvarez

发明人： Alain Porte ,  Jacques Lalane ,  Franck Alvarez

IPC分类号： B64D29/00 ,  B64D29/08

CPC分类号： B64D29/06 ,  B64D29/08

摘要： The object of the invention is an aircraft nacelle that comprises at least one part, called a door (14), that moves relative to a stationary part (20) and a connecting device that makes it possible to limit the offset between said door and said stationary part in a direction that corresponds to the primary direction of the flow of air outside of the nacelle during flight, whereby said device comprises, on the one hand, an indexer (40) that is connected to the door (14) that comprises an attachment surface (63) and at least one attachment element (66), and, on the other hand, at least one stop (58) that is connected to the stationary part (20) against which said indexer (40) can rest in such a way as to limit its movement in said direction, characterized in that said at least one attachment element (66), oriented in the radial direction, is arranged upstream from the stop (58) in said direction, said at least one stop (58) comprising a surface relative to the door arranged essentially at the attachment surface (63) of the indexer (40).

摘要翻译： 本发明的目的是一种飞机机舱，其包括称为门（14）的至少一部分，其相对于静止部分（20）和连接装置移动，所述连接装置使得可以限制所述门和所述第二门 固定部分在与飞行中的机舱外部的空气流的主要方向对应的方向上，其中所述装置一方面包括连接到门（14）的分度器（40），该分度器包括一个 附接表面（63）和至少一个附接元件（66），另一方面，连接到所述固定部分（20）的至少一个止动件（58），所述分度器（40）能够抵靠所述固定部分 一种限制其在所述方向上移动的方式，其特征在于，所述至少一个在径向方向上定向的连接元件（66）沿着所述方向设置在止动件（58）的上游，所述至少一个止动件 ）包括相对于所述门的表面，其基本上a布置 t分度器（40）的附接表面（63）。

公开(公告)号：US08172037B2

公开(公告)日：2012-05-08

申请号：US12663608

申请日：2008-06-03

申请人： Alain Porte ,  Jacques Lalane

发明人： Alain Porte ,  Jacques Lalane

IPC分类号： B64D15/04

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

摘要： The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer (28), at least one cellular structure (30) and a reflective layer (32), characterized in that it comprises ducts (34) provided between said cellular structure (30) and the acoustically resistive structure (28), the ducts being each defined by a wall (36) separate from the walls of the cellular structure (30) and one end of the ducts being connected to a hot air supply.

摘要翻译： 本发明涉及一种用于在飞机表面，特别是在诸如飞机机舱的进气口的前缘处进行声学处理的涂层，所述涂层包括声阻层（28），至少一个多孔结构（30 ）和反射层（32），其特征在于，其包括设置在所述多孔结构（30）和所述声阻结构（28）之间的管道（34），所述管道各自由与壁分离的壁（36）限定 的多孔结构（30），并且所述管道的一端连接到热空气源。

公开(公告)号：US20110139940A1

公开(公告)日：2011-06-16

申请号：US12990562

申请日：2009-04-28

申请人： Alain Porte ,  Jacques Lalane

发明人： Alain Porte ,  Jacques Lalane

IPC分类号： B64D33/02 ,  B64D29/00 ,  B64C1/40

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  F02C7/045 ,  Y02T50/671

摘要： An aircraft nacelle includes an air intake for channeling air flow in the direction of a power plant. The air intake includes an inside pipe that forms an aerodynamic surface in contact with the air flow and is extended toward the rear by an aerodynamic surface of a pipe of the power plant. The nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel.

摘要翻译： 飞机机舱包括用于在发电厂的方向引导空气流的进气口。 进气口包括形成与气流接触的空气动力学表面的内部管道，并且通过发电厂的管道的空气动力学表面向后延伸。 所述机舱包括波衰减面板，其限制或防止在所述发电厂泵送期间产生的至少一个波的传播，并且包括与所述气流接触的层，所述层可允许所述至少一个波的通过， 至少一个肺泡结构，以及反射或不渗透层，其中波浪衰减面板插入在进气口和发电厂之间，并且与气流接触的层确保布置在下游的空气动力学表面的连续性 并且上游波浪衰减面板包括可以插入在进气口和发电厂之间的插入件，以便不粉碎波浪衰减面板。