公开(公告)号：US20090255589A1

公开(公告)日：2009-10-15

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： F02C7/04

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

摘要： According to the invention, the internal wall of the air intake (2) and the housing of the fan (3) form a single tubular piece (30) made from a fibre/resin composite material.

摘要翻译： 根据本发明，进气口（2）的内壁和风扇（3）的壳体形成由纤维/树脂复合材料制成的单个管状件（30）。

公开(公告)号：US08628635B2

公开(公告)日：2014-01-14

申请号：US13147471

申请日：2010-01-29

申请人： Frederic Chelin ,  Christophe Menier ,  Jean Yves Thomy ,  Etienne Bertin ,  Thierry Surply ,  Dominique Haro ,  Fabrice Gantie

发明人： Frederic Chelin ,  Christophe Menier ,  Jean Yves Thomy ,  Etienne Bertin ,  Thierry Surply ,  Dominique Haro ,  Fabrice Gantie

IPC分类号： B29C70/30

CPC分类号： B29D24/005 ,  B29C70/30 ,  B29L2031/3076 ,  B32B3/12 ,  B32B3/266 ,  B32B3/28 ,  B32B5/22 ,  B32B5/24 ,  B32B5/26 ,  B32B7/045 ,  B32B7/14 ,  B32B15/04 ,  B32B15/08 ,  B32B15/14 ,  B32B27/06 ,  B32B37/146 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/10 ,  B32B2605/18 ,  B64D2033/0206 ,  B64D2033/0233 ,  Y10T156/1039

摘要： A process for producing a panel for acoustic treatment including a resistive porous layer, an alveolar structure, a reflective layer with openings, and a drainage plate having a furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film a core whose cross-section is adapted to that of the evacuation pipe so that the core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the core, demolding the drainage plate and removing the core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.

摘要翻译： 一种用于制造用于声处理的面板的方法，包括电阻性多孔层，肺泡结构，具有开口的反射层，以及具有沟槽的排水板，当排水板平坦化为至少一个抽空管时， 反射层包括：根据其最终几何形状使反射层成形，将脱模膜固定在反射层的自由表面的至少一部分上，将脱模膜定位在芯上，芯的横截面适应于 抽出管，使得芯覆盖反射层的开口，在脱模膜和芯上成型排水板，使排水板脱模并除去芯和脱模膜，并使排水板与自由表面一体化 的反射层。

公开(公告)号：US20120152443A1

公开(公告)日：2012-06-21

申请号：US13147471

申请日：2010-01-29

申请人： Frederic Chelin ,  Christophe Menier ,  Jean Yves Thomy ,  Etienne Bertin ,  Thierry Surply ,  Dominique Haro ,  Fabrice Gantie

发明人： Frederic Chelin ,  Christophe Menier ,  Jean Yves Thomy ,  Etienne Bertin ,  Thierry Surply ,  Dominique Haro ,  Fabrice Gantie

IPC分类号： B29C70/30

CPC分类号： B29D24/005 ,  B29C70/30 ,  B29L2031/3076 ,  B32B3/12 ,  B32B3/266 ,  B32B3/28 ,  B32B5/22 ,  B32B5/24 ,  B32B5/26 ,  B32B7/045 ,  B32B7/14 ,  B32B15/04 ,  B32B15/08 ,  B32B15/14 ,  B32B27/06 ,  B32B37/146 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/10 ,  B32B2605/18 ,  B64D2033/0206 ,  B64D2033/0233 ,  Y10T156/1039

摘要： A process for producing a panel for acoustic treatment including an acoustically resistive porous layer, at least one alveolar structure, a reflective layer with openings, and a drainage plate having at least one furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping, if necessary, the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film at least one core whose cross-section is adapted to that of the evacuation pipe so that the at least one core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the at least one core, demolding the drainage plate and removing the at least one core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.

摘要翻译： 一种用于声学处理的制造方法，包括：声阻性多孔层，至少一个肺泡结构，具有开口的反射层，以及排水板，当排水板变平时，至少有一个沟槽限定至少一个排气管 反射层的自由表面包括：如有必要，根据其最终几何形状将反射层成形，将脱模膜固定在反射层的自由表面的至少一部分上，至少在脱模膜上定位 一个核心，其横截面适合于排气管的核心，使得至少一个核心覆盖反射层的开口，在脱模膜和至少一个芯上模制排水板，使排水板脱模和去除 所述至少一个芯和所述脱模膜，并且使所述排水板与所述反射层的自由表面成一体。

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：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。

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：US20100038476A1

公开(公告)日：2010-02-18

申请号：US12440354

申请日：2007-09-06

申请人： Fabrice Gantie ,  Yann Druon

发明人： Fabrice Gantie ,  Yann Druon

IPC分类号： B64C1/40 ,  F02C7/24

CPC分类号： F04D29/662 ,  F02C7/24 ,  F02K1/44 ,  F02K1/827 ,  F02K3/04 ,  F05D2230/90 ,  F05D2240/126 ,  F05D2250/33 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/671

摘要： A device for improving the effectiveness of the acoustic treatment(s) in an aircraft propulsion unit that includes a pipe (36) into which a gas stream flows, whereby the pipe (36) is delimited by two approximately concentric inside walls (40) and outside walls (42), wherein the device includes at least one partition (38, 38′) that extends over at least one portion of the length of the pipe (36) between the inside and outside walls (40, 42) and in that the profile of at least one wall (44, 46) of the at least one partition (38, 38′) is defined so as to increase the number of reflections of an acoustic beam on at least one of the inside and/or outside walls (40, 42) of the pipe and/or on at least one of the walls (44, 46) of the at least one partition (38, 38′).

摘要翻译： 一种用于提高飞机推进装置中的声学处理效果的装置，该装置包括气流流入的管道（36），由此管道（36）由两个近似同心的内壁（40）界定， 外壁（42），其中所述装置包括在所述内壁和外壁（40,42）之间的所述管（36）的长度的至少一部分上延伸的至少一个隔板（38,38'），并且因此 所述至少一个分隔件（38,38'）的至少一个壁（44,46）的轮廓被限定为增加在所述内壁和/或外壁中的至少一个上的声束的反射次数 （40,42）和/或至少一个隔板（38,38'）的至少一个壁（44,46）上。

公开(公告)号：US09003760B2

公开(公告)日：2015-04-14

申请号：US13145685

申请日：2010-01-29

申请人： Frédéric Chelin ,  Thierry Surply ,  Dominique Haro ,  Fabrice Gantie ,  David Lambert

发明人： Frédéric Chelin ,  Thierry Surply ,  Dominique Haro ,  Fabrice Gantie ,  David Lambert

IPC分类号： B64D15/04 ,  F02C7/047 ,  F02C7/045 ,  B64D33/02 ,  F02K1/82

CPC分类号： B64D33/02 ,  B64D15/04 ,  B64D2033/0206 ,  B64D2033/0233 ,  F02C7/045 ,  F02C7/047 ,  F02K1/827 ,  Y10T137/0536

摘要： An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.

摘要翻译： 连接到飞机机舱的进气口的声学处理面板包括至少一个声阻构造（30）和反射层（32），它们位于基本垂直于纵向方向的方向上 （34）的肺泡细胞间隔开以允许用于霜冻治疗的热空气的通过，其特征在于，其包括用于热空气的管（36），每个管（36）分别由至少一个 隔板从隔音层（30）延伸到反射层（32），以使得单元的带（34）在纵向方向上绝缘。

公开(公告)号：US08733688B2

公开(公告)日：2014-05-27

申请号：US12515031

申请日：2007-11-13

申请人： Fabrice Gantie ,  Alain Porte

发明人： Fabrice Gantie ,  Alain Porte

IPC分类号： B64C1/40 ,  B64C23/00

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：US08181900B2

公开(公告)日：2012-05-22

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： B64C1/40 ,  B64C23/40 ,  B64D15/00

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 characterized 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。