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    Aircraft nacelle including an optimised acoustic processing system
    5.
    发明授权
    Aircraft nacelle including an optimised acoustic processing system 有权
    飞机机舱包括优化的声学处理系统

    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）。

    AIRCRAFT NACELLE INCLUDING AN OPTIMISED ACOUSTIC PROCESSING SYSTEM
    6.
    发明申请
    AIRCRAFT NACELLE INCLUDING AN OPTIMISED ACOUSTIC PROCESSING SYSTEM 有权
    包括优化声学处理系统的飞机制造商

    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）。

    AIRCRAFT LEADING EDGE
    7.
    发明申请
    AIRCRAFT LEADING EDGE 有权
    飞机领先

    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） 。

    COATING FOR ACOUSTIC TREATMENT HAVING A HOT AIR ICING PROCESSING FUNCTION OF FROST TREATMENT WITH HOT AIR
    8.
    发明申请
    COATING FOR ACOUSTIC TREATMENT HAVING A HOT AIR ICING PROCESSING FUNCTION OF FROST TREATMENT WITH HOT AIR 有权
    用于具有热空气的热处理功能的热疗处理功能的涂层

    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）。

    Acoustic processing structure particularly adapted to the air inlet of an aircraft nacelle
    10.
    发明授权
    Acoustic processing structure particularly adapted to the air inlet of an aircraft nacelle 有权
    声学处理结构特别适用于飞机机舱的进气口

    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。