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：US08505679B2

公开(公告)日：2013-08-13

申请号：US13514765

申请日：2010-12-20

申请人： Alain Porte ,  Cedric Leconte

发明人： Alain Porte ,  Cedric Leconte

IPC分类号： B64D33/02

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  F02C7/045 ,  F05D2260/96

摘要： An aircraft nacelle includes an air inlet (110) with a lip (114) extended to the back by a passage (116) to channel an air flow to a drive (112), the passage having at least one acoustic treatment panel (120) that includes, from the outside to the inside: an acoustically resistant porous layer (122); at least one cell-like structure (124), whose cells are sized for acoustic treatment; and a reflective or sealed layer (126). The reflective layer includes, near the end thereof that is oriented toward the lip, a surface (130) that is angled so as to be connected to the lip. A cell-like structure (136) is in contact with the angled surface, which forms an angle less than 30° with the tangent on the acoustically resistant layer. The cell-like structure is inserted between the angled surface of the reflective layer and an acoustically resistant porous layer.

摘要翻译： 飞机机舱包括具有通过通道（116）向后延伸以将空气流引导到驱动器（112）的唇缘（114）的空气入口（110），该通道具有至少一个声学处理面板（120） 从外部到内部包括：抗声多孔层（122）; 至少一个细胞样结构（124），其细胞的尺寸用于声学处理; 和反射或密封层（126）。 反射层在靠近唇缘的端部附近包括倾斜的表面，以便连接到唇部。 细胞状结构（136）与成角度的表面接触，其与抗电阻层上的切线形成小于30°的角度。 将电池状结构插入在反射层的倾斜表面和抗声多孔层之间。

公开(公告)号：US08448901B2

公开(公告)日：2013-05-28

申请号：US12745953

申请日：2008-12-01

申请人： Alain Porte ,  Gilles Chene ,  Arnaud Hormiere

发明人： Alain Porte ,  Gilles Chene ,  Arnaud Hormiere

IPC分类号： B64D15/02

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

摘要： The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which the two members are superimposed, both members each having a surface defining the outer surface of the nacelle on either side of the junction area, characterized in that said discharge means (50) includes a dual-portion shim (52), i.e. a first portion provided between the superimposed panels and including at least one protruding and/or recessed member for forming a passage between said panels in order to establish a communication between the inside and the outside of the nacelle, and a second portion at the level of only one panel, i.e. that located inside at the junction area, in order to protect the same against excessive temperatures.

摘要翻译： 本发明涉及一种飞机机舱，其包括用于在机舱内部和其外部之间建立连通的排放装置（50）和两个构件（54,56）之间的连接区域，并且两个构件 叠加的两个构件各自具有限定在接合区域的任一侧上的机舱的外表面的表面，其特征在于，所述排出装置（50）包括双重部分垫片（52），即设置在叠置 板，并且包括至少一个突出和/或凹入的构件，用于在所述面板之间形成通道，以便建立机舱的内部和外部之间的连通，以及仅在一个面板的水平处的第二部分，即位于 在交汇处内部，以保护相同的温度过高。

公开(公告)号：US20130033036A1

公开(公告)日：2013-02-07

申请号：US13566410

申请日：2012-08-03

申请人： Alain Porte ,  Stéphane Dida ,  Matthieu Fargues ,  Martial Marro

发明人： Alain Porte ,  Stéphane Dida ,  Matthieu Fargues ,  Martial Marro

IPC分类号： F16L23/036 ,  F02C7/04

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/047 ,  F05D2240/14 ,  F16B2200/50 ,  F16B2200/506 ,  Y02T50/672

摘要： A fastening device includes an annular flange connected to an air intake, an annular flange connected to a powerplant pressed against the annular flange and fastening elements that allow the annular flanges to be linked, and for at least a first fastening element, a blade is fitted between the fastening element and the annular flange, the blade consisting of at least a central part linked to the first fastening element, radially mobile relative to the annular flange, and at least one part offset for which at least radial centripetal displacement is limited relative to the annular flange, the two parts being offset along the direction of the circumference.

摘要翻译： 紧固装置包括连接到进气口的环形凸缘，连接到压靠环形凸缘的动力装置的环形凸缘和允许环形凸缘连接的紧固元件，并且至少第一紧固元件安装有叶片 在所述紧固元件和所述环形凸缘之间，所述叶片由至少连接到所述第一紧固元件的中心部分相对于所述环形凸缘径向移动，以及至少一个偏移部分，所述至少一个偏移部分相对于 环形凸缘，两个部分沿圆周方向偏移。

公开(公告)号：US08366039B2

公开(公告)日：2013-02-05

申请号：US12305903

申请日：2007-06-18

申请人： Alain Porte

发明人： Alain Porte

IPC分类号： B64D27/00

CPC分类号： B64D29/06 ,  B64D27/18

摘要： Disclosed is a pylon fairing for a turbine engine. The anterior portion of the pylon fair is attached to a turbine engine in a manner to absorb blows against the fan casing of the turbine engine in case of breakage of the fan blades of the turbine engine. The pylon fairing is configured with the turbine engine such that the anterior part of the pylon fairing is fastened to the engine's fan casing via a front fixing and a rear fixing. The rear fixing is affixed to the fan casing as relatively loose in order to absorb tolerances, and the front fixing is affixed to the fan casing and as flexible in at least approximately a radial direction with respect to the fan casing.

摘要翻译： 公开了一种用于涡轮发动机的塔架整流罩。 在塔式发电机的风扇叶片断裂的情况下，塔架的前部部分以一种吸附涡轮发动机的风扇壳体的方式附接到涡轮发动机。 塔架整流罩配置有涡轮发动机，使得塔架整流罩的前部通过前固定和后固定固定到发动机的风扇壳体。 为了吸收公差，后部固定件相对较松地固定到风扇壳体上，并且前部固定件固定到风扇壳体上，并且相对于风扇壳体至少沿大致径向的方向固定。

公开(公告)号：US20110253843A1

公开(公告)日：2011-10-20

申请号：US13122885

申请日：2009-10-05

申请人： Alain Porte ,  Emeric Chancerelle ,  Franck Alvarez ,  Damien Prat

发明人： Alain Porte ,  Emeric Chancerelle ,  Franck Alvarez ,  Damien Prat

IPC分类号： B64D33/02

CPC分类号： B64D33/08 ,  B64D2241/00 ,  Y10T137/0536

摘要： The invention relates to an arrangement (1) that comprises a mobile plate (18) controlled by a means for fluid communication (23) between the outer (18A) and inner surfaces of the mobile plate (18), wherein said means is located at least in the vicinity of a limited downstream area (24) of said outer surface (18A), are at a high pressure when the aircraft flies at cruising speed, and are capable of transmitting said high pressure to an extended area (26) of said inner surface.

摘要翻译： 本发明涉及一种装置（1），其包括由可移动板（18）的外部（18A）和内表面之间的流体连通装置（23）控制的移动板（18），其中所述装置位于 至少在所述外表面（18A）的有限的下游区域（24）附近，当飞机以巡航速度飞行时处于高压，并且能够将所述高压传递到所述外表面的延伸区域（26） 内表面。

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：US20110116916A1

公开(公告)日：2011-05-19

申请号：US13054333

申请日：2009-07-15

申请人： Alain Porte ,  Robert Andre ,  Matthieu Fargues

发明人： Alain Porte ,  Robert Andre ,  Matthieu Fargues

IPC分类号： F01D25/24

CPC分类号： B64D29/06

摘要： An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes: a flexible element that follows the curved profile of the door between two remote anchoring points, at least one safety index including a latch pivotable around an axis of rotation, and connected to the door so as to occupy a locked position in which the end of the latch rests against the inside surface of an edge upstream from the door, and an unlocked position in which the end of the latch is offset relative to the edge, whereby in the locked position, the latch prevents the scooping phenomena by limiting movements of the door in the radial direction toward the outside of the nacelle, and elements for stretching the flexible element between the two anchoring points and for controlling the pivoting in the locked position of the latch.

摘要翻译： 飞机机舱包括进气口，其后部在上部，与被称为盖的桅杆成一体的部分，以及至少一个具有弯曲轮廓的门，该门具有布置在门上游边缘处的加强装置， 包括：在两个远程锚固点之间跟随门的弯曲轮廓的柔性元件，至少一个安全索引，其包括围绕旋转轴线枢转的闩锁，并且连接到门以便占据锁定位置，在该位置， 闩锁抵靠门上游边缘的内表面，以及解锁位置，其中闩锁的端部相对于边缘偏移，由此在锁定位置，闩锁通过限制闩锁的动作来防止舀起现象 门朝向机舱外侧的径向方向，以及用于在两个锚固点之间拉伸柔性元件并用于控制在锁定位置的枢转的元件 的闩锁。

公开(公告)号：US07926261B2

公开(公告)日：2011-04-19

申请号：US12067931

申请日：2006-09-13

申请人： Alain Porte

发明人： Alain Porte

IPC分类号： F02K3/02

CPC分类号： F01D9/065 ,  B64D13/06 ,  F02C6/08 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F28D7/1615 ,  F28D7/1669 ,  F28D7/1684 ,  F28D2021/0021 ,  Y02T50/675

摘要： The invention is a turbofan provided with a pre-cooler. In order to evacuate the heated cool air stream, at least one discharge pipe is arranged in a chamber and connects the pre-cooler to at least one discharge orifice provided in the inner fairing, in output of an exhaust nozzle and at least more or less opposite the wing.

摘要翻译： 本发明是一种具有预冷器的涡轮风扇。 为了排出加热的冷空气流，至少一个排放管布置在室中，并将预冷器连接到设置在内部整流装置中的至少一个排出孔，并且在排气喷嘴的输出中至少或多或少地 在机翼对面

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。