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：US09010084B2

公开(公告)日：2015-04-21

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： F02K3/02 ,  B64D15/04 ,  B64D33/02

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：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：US20100000227A1

公开(公告)日：2010-01-07

申请号：US12307881

申请日：2007-07-04

申请人： Alain Porte ,  Jacques Lalane ,  Fabrice Gantie

发明人： Alain Porte ,  Jacques Lalane ,  Fabrice Gantie

IPC分类号： F02C7/20 ,  F01D1/02

CPC分类号： F02C7/04 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  F05D2230/60 ,  F05D2240/14 ,  F05D2300/603 ,  Y02T50/672

摘要： According to the invention, the air intake (2) is made of a piece (23) of fibre/resin composite material, reinforced on the side of the flange (24) by a reinforcing ring (26).

摘要翻译： 根据本发明，进气口（2）由纤维/树脂复合材料片（23）制成，通过加强环（26）在凸缘（24）侧加强。

公开(公告)号：US20100116587A1

公开(公告)日：2010-05-13

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： The invention relates to a panel for an acoustic treatment at the surface of an aircraft, that comprises from the outside to the inside an acoustically resistive porous layer, at least one cellular structure and a reflective or non-permissive layer, wherein the acoustically resistive porous layer includes, at the outer surface that may contact the aerodynamic flows of a sheet or foil, open areas (14) permissive to sound waves and solid area (6) not permissive to sound waves, characterised in that the sheet or foil of the acoustically resistive layer includes sets of microperforations (18), each set of microperforations defining an open area (14), the set of microperforations being separated by at least one series of spaced bands of solid areas (16).

摘要翻译： 本发明涉及一种用于在飞行器表面处进行声学处理的面板，其包括从外部到内部的声阻多孔层，至少一个蜂窝结构和反射或非允许层，其中所述声阻多孔 在可能接触片材或箔片的空气动力学流动的外表面处包括允许声波的开放区域（14）和不允许声波的固体区域（6），其特征在于，声学的片材或箔片 电阻层包括一组微穿孔（18），每套微穿孔限定开放区域（14），所述一组微穿孔由至少一系列间隔的固体区域（16）分隔开。

公开(公告)号：US20100089690A1

公开(公告)日：2010-04-15

申请号：US12527984

申请日：2008-02-14

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 ,  G06F17/50

CPC分类号： F02C7/045 ,  B64D2033/0206 ,  F02C7/047 ,  F05D2230/60 ,  F05D2250/282 ,  F05D2250/283 ,  F05D2250/32 ,  F05D2250/60 ,  F05D2250/71 ,  G10K11/172 ,  Y02T50/672

摘要： A process for the producing a coating for acoustic treatment relative to a leading edge such as an air intake of an aircraft nacelle, the coating including a reflective layer, an alveolar structure, and an acoustically resistive layer, includes:Digitizing the shape of the alveolar structure that it will have when it will be installed at the surface to be treated,Positioning in a virtual manner—so as to define their geometries—two series of bands so as to delimit a tube between, two adjacent bands of a first series, and two second adjacent bands of a second series,Cutting out each band according to their geometries defined above,Producing cut-outs in each band to allow the assembly of the bands,Assembling the bands so as to obtain an alveolar structure that has shapes that are suited to the surface to be treated.

摘要翻译： 一种用于制造用于声学处理的涂层的方法，所述涂层相对于诸如飞机机舱的进气口的前缘，所述涂层包括反射层，肺泡结构和声阻层，包括：数字化肺泡的形状 当它将被安装在待处理的表面时将具有的结构 - 以虚拟的方式定位 - 以便限定它们的几何 - 两个系列的带，以便在第一系列的两个相邻带之间界定管， 和第二系列的两个第二相邻带，根据其上述的几何形状切割每个带，在每个带中产生切口以允许带的组装，组装条带以获得具有形状的肺泡结构 适合于待处理的表面。

公开(公告)号：US08413922B2

公开(公告)日：2013-04-09

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 ,  B64D15/04

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：US20100294882A1

公开(公告)日：2010-11-25

申请号：US12515031

申请日：2007-11-13

申请人： Fabrice Gantie ,  Alain PORTE ,  Alain Porte

发明人： Fabrice Gantie ,  Alain PORTE ,  Alain Porte

IPC分类号： F02C7/045 ,  B64D15/16 ,  B64D33/02

CPC分类号： B64D33/02 ,  B64D15/163 ,  B64D2033/0206 ,  B64D2033/0233 ,  B64D2033/0286 ,  F02C7/045 ,  F02C7/047 ,  G10K11/172

摘要： An aircraft leading edge, such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, includes a coating (26) for the acoustic treatment that includes—from the outside to the inside—an acoustically resistive porous layer that has a determined open surface ratio, at least one alveolar structure, and a reflective layer, whereby the coating (26) integrates a frost treatment system, characterized in that a frost treatment system includes at least one vibration emitter (36).

摘要翻译： 飞行器前缘，例如推进单元的机舱（14）的进气口（22）包括用于声学处理的涂层（26），其包括从外部到内部的声学处理 具有确定的开放表面比的电阻性多孔层，至少一个肺泡结构和反射层，由此所述涂层（26）集成了霜冻处理系统，其特征在于，霜冻处理系统包括至少一个振动发射器（36） 。

公开(公告)号：US20100301161A1

公开(公告)日：2010-12-02

申请号：US12515035

申请日：2007-11-13

申请人： Gilles Chene ,  Fabrice Gantie ,  Alain Porte

发明人： Gilles Chene ,  Fabrice Gantie ,  Alain Porte

IPC分类号： F02C7/045 ,  B64D15/00 ,  B64D33/02 ,  B64D15/12

CPC分类号： B64D33/02 ,  B64D15/12 ,  B64D2033/0206 ,  B64D2033/0233 ,  B64D2033/0286 ,  F02C7/045 ,  F02C7/047 ,  F05D2260/96 ,  G10K11/172 ,  Y02T50/672

摘要： The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least one cellular structure (30) and an acoustically resistive structure (32) having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer (46) comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterised in that the acoustically resistive structure (32) includes at least one structural layer (36) with openings (38) and in that said at least one heating layer (46) is disposed under the structural layer (36).

摘要翻译： 本发明涉及一种用于飞机的声衬，其可以覆盖前缘，例如推进单元的机舱中的空气入口，所述衬里包括：（i）从内向外的反射层（28），在 至少一个蜂窝结构（30）和具有预定比例的开放表面的声阻结构（32）; 以及（ii）至少一个形式为至少一个加热层（46）形式的霜冻处理系统，所述加热层包括声波可穿过的开放区域，所述开口区域至少部分地与声阻结构中的开放区域协作。 本发明的特征在于，声阻结构（32）包括具有开口（38）的至少一个结构层（36），并且所述至少一个加热层（46）设置在结构层（36）下方。