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：US20100096213A1

公开(公告)日：2010-04-22

申请号：US12528007

申请日：2008-02-14

申请人： Valerie Frustie ,  Bemard Duprieu ,  Fabrice Gantie

发明人： Valerie Frustie ,  Bemard Duprieu ,  Fabrice Gantie

IPC分类号： B64D33/02

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  F02C7/047 ,  F05D2250/283 ,  F05D2260/96

摘要： A coating for acoustic treatment relative to an aircraft's surface, in particular a leading edge such as an air intake of an aircraft nacelle, includes an acoustically resistive layer, at least one alveolar structure (30), and a reflective layer. The alveolar structure (30) includes a number of tubes that empty out, on the one hand, at a first imaginary surface (34), and, on the other hand, at a second imaginary surface (36). The alveolar structure (30) includes cut-outs or openings (38) made at the side walls of certain tubes that make it possible to link adjacent tubes so as to create a network of communicating tubes that isolate at least one tube or a group of non-communicating tubes, whereby at least one of the communicating tubes is connected to at least one hot gas intake (40).

摘要翻译： 用于相对于飞行器表面，特别是诸如飞机机舱的进气口的前缘的声学处理的涂层包括声阻层，至少一个肺泡结构（30）和反射层。 肺泡结构（30）包括多个管，一方面在第一假想表面（34）处，另一方面在第二假想表面（36）处排空。 肺泡结构（30）包括在某些管的侧壁处制成的切口或开口（38），使得可以连接相邻的管，以便形成连通管的网络，其隔离至少一个管或一组 非连通管，其中至少一个连通管连接到至少一个热气体进口（40）。

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：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：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：US07938224B2

公开(公告)日：2011-05-10

申请号：US12528007

申请日：2008-02-14

申请人： Valerie Frustie ,  Bernard Duprieu ,  Fabrice Gantie

发明人： Valerie Frustie ,  Bernard Duprieu ,  Fabrice Gantie

IPC分类号： B64D33/02

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  F02C7/047 ,  F05D2250/283 ,  F05D2260/96

摘要： A coating for acoustic treatment relative to an aircraft's surface, in particular a leading edge such as an air intake of an aircraft nacelle, includes an acoustically resistive layer, at least one alveolar structure (30), and a reflective layer. The alveolar structure (30) includes a number of tubes that empty out, on the one hand, at a first imaginary surface (34), and, on the other hand, at a second imaginary surface (36). The alveolar structure (30) includes cut-outs or openings (38) made at the side walls of certain tubes that make it possible to link adjacent tubes so as to create a network of communicating tubes that isolate at least one tube or a group of non-communicating tubes, whereby at least one of the communicating tubes is connected to at least one hot gas intake (40).

摘要翻译： 用于相对于飞行器表面，特别是诸如飞机机舱的进气口的前缘的声学处理的涂层包括声阻层，至少一个肺泡结构（30）和反射层。 肺泡结构（30）包括多个管，一方面在第一假想表面（34）处，另一方面在第二假想表面（36）处排空。 肺泡结构（30）包括在某些管的侧壁处制成的切口或开口（38），使得可以连接相邻的管，以便形成连通管的网络，其隔离至少一个管或一组 非连通管，其中至少一个连通管连接到至少一个热气体进口（40）。

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：US08167232B2

公开(公告)日：2012-05-01

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

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：US20120090693A1

公开(公告)日：2012-04-19

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： F02K99/00 ,  E04B1/82

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：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）。