公开(公告)号：US09162747B2

公开(公告)日：2015-10-20

申请号：US14093749

申请日：2013-12-02

Applicant: Aircelle

Inventor： Franck Maze ,  John Moutier

IPC: B64D33/02 ,  B29C51/14 ,  B64C1/40 ,  B32B3/12 ,  F02K1/82 ,  G10K11/168 ,  F02C7/045 ,  B64F5/00 ,  B32B3/02 ,  B64D33/00

CPC classification number: B64C1/40 ,  B32B3/02 ,  B32B3/12 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/102 ,  B32B2605/18 ,  B64F5/00 ,  F02C7/045 ,  F02K1/827 ,  G10K11/168 ,  Y02T50/672

Abstract: The present disclosure provides a method for manufacturing a sound attenuation panel having a first cellular core structure and a second cellular core structure joined in a junction area (J). The method includes: a) a joining edge of the first cellular core structure is joined to a corresponding joining edge of the second cellular core structure, thereby forming the junction area; b) the first cellular core structure and the second cellular core structure are placed between an inner skin and an outer skin of the panel.In particular, the method further has a step prior to step a), in which one junction reinforcement is inserted between the joining edge of the first cellular core structure and the corresponding joining edge of the second cellular core structure in the junction area.

Abstract translation: 本公开提供一种用于制造具有连接在接合区域（J）中的第一蜂窝状芯结构和第二蜂窝状芯结构的声音衰减板的方法。 该方法包括：a）第一多孔芯结构的接合边缘连接到第二多孔芯结构的对应接合边缘，由此形成接合区域; b）第一细胞芯结构和第二细胞核结构放置在面板的内皮和外皮之间。 特别地，该方法还具有步骤a）之前的步骤，其中一个接合加强件插入在第一多孔芯结构的接合边缘和第二多孔芯结构的接合区域的相应接合边缘之间。

公开(公告)号：US09109509B2

公开(公告)日：2015-08-18

申请号：US13671233

申请日：2012-11-07

Applicant: AIRCELLE

Inventor： Christophe Thorel ,  Bertrand Desjoyeaux ,  Florent Bouillon ,  John Moutier ,  Stéphane Bardin

IPC: B64D33/02 ,  F02C7/04 ,  B64D29/06 ,  F02C7/045 ,  F02K1/80 ,  F02K1/82

CPC classification number: F02C7/04 ,  B64D29/06 ,  F02C7/045 ,  F02K1/80 ,  F02K1/827 ,  Y02T50/672 ,  Y10T29/49826 ,  Y10T403/45

Abstract: A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule.

Abstract translation: 提供了一种用于飞机推进器的单元，其包括构造成附接到第二套圈的第一套圈和构造成固定到固定到第二套圈的第二对应连接凸缘的第一连接凸缘。 连接凸缘包括形成相对于第一套圈沿径向方向延伸的平面的部分。 第一套圈和对应的连接凸缘之间的连接偏移到与所述平面相对应的距离，该长度与用于阻尼通过第一套圈的力的通量产生的剪切产生弯曲力矩的长度相对应。

公开(公告)号：US09518509B2

公开(公告)日：2016-12-13

申请号：US14635667

申请日：2015-03-02

Applicant: AIRCELLE

Inventor： Bertrand Desjoyeaux ,  Thierry Deschamps ,  John Moutier

IPC: F02C7/04 ,  B32B3/12 ,  B32B3/18 ,  F02K1/82 ,  G10K11/172 ,  B32B37/12 ,  B32B38/00 ,  B32B5/14 ,  B32B5/24 ,  B32B7/12 ,  B32B15/04 ,  B32B15/14 ,  B32B15/20 ,  B32B3/26

CPC classification number: F02C7/04 ,  B32B3/12 ,  B32B3/18 ,  B32B3/266 ,  B32B5/142 ,  B32B5/24 ,  B32B7/12 ,  B32B15/04 ,  B32B15/14 ,  B32B15/20 ,  B32B37/12 ,  B32B38/0012 ,  B32B2038/0052 ,  B32B2307/102 ,  B32B2307/50 ,  B32B2307/546 ,  B32B2307/724 ,  B32B2307/7242 ,  B32B2605/18 ,  F02K1/827 ,  G10K11/172 ,  Y02T50/672 ,  Y10T137/0536 ,  Y10T156/1003 ,  Y10T428/192 ,  Y10T428/24149

Abstract: The present disclosure related to a method for manufacturing a structure with cellular cores that can be used in a structural panel of a turbojet nacelle, including at least one block of cellular cores. The at least one block of cellular cores includes a central portion with core honeycomb cells, and two side portions each including side honeycomb cells. The side honeycomb cells have edge honeycomb cells situated on edges of a side part of a block, and adjacent honeycomb cells. In particular, the method includes: A) forming junction walls on the side honeycomb cells by opening the edge honeycomb cells, the junction walls being capable of interacting for forming a junction area; B) unfolding the junction walls thus formed in step A; and C) joining the junction walls thus unfolded in step B and belonging to two different side portions end-to-end.

Abstract translation: 本公开涉及一种用于制造具有蜂窝芯的结构的方法，所述结构可以用于包括至少一个蜂窝芯的块的涡轮喷气发动机舱的结构面板中。 所述至少一个蜂窝芯块包括具有核心蜂窝单元的中心部分，以及包括侧蜂窝单元的两个侧部分。 侧蜂窝单元具有位于块的侧部的边缘上的边缘蜂窝单元和相邻的蜂窝单元。 特别地，该方法包括：A）通过打开边缘蜂窝单元在侧蜂窝单元上形成接合壁，所述接合壁能够相互作用以形成接合区域; B）在步骤A中展开由此形成的接合壁; 并且C）在步骤B中连接如此展开的接合壁并且属于端对端的两个不同的侧部。

公开(公告)号：US08636107B2

公开(公告)日：2014-01-28

申请号：US13941044

申请日：2013-07-12

Applicant: Aircelle

Inventor： John Moutier ,  Emmanuel Anfray ,  Franck Maze ,  Herve Simon

IPC: E04B1/84 ,  B32B43/00 ,  E04B1/74

CPC classification number: F02C7/24 ,  B29C73/04 ,  B29C73/26 ,  B64D2033/0206 ,  B64F5/40 ,  Y10T29/49398 ,  Y10T29/49618 ,  Y10T29/49732 ,  Y10T29/49734 ,  Y10T156/1082

Abstract: The present disclosure relates to a method for repairing a portion of an acoustic panel for a nacelle of an aircraft turbojet engine. The panel includes an acoustic skin in which a plurality of acoustic holes are drilled, a solid skin, and a cellular acoustic structure. The cellular acoustic structure, being arranged between the acoustic skin and the solid skin, has a plurality of cells, each of which has one or more drainage openings arranged in one or more of the walls forming each cell. The method includes a step of: defining a part of the acoustic panel to be cut; forming a cutting area closed by the acoustic skin; injecting a resin through the acoustic holes; positioning a replacement cellular acoustic structure in the cutting area and on the acoustic skin; forming a solid replacement skin on the replacement cellular acoustic structure.

Abstract translation: 本公开涉及一种用于修理飞机涡轮喷气发动机的机舱的声学面板的一部分的方法。 面板包括其中钻有多个声孔的声学皮肤，固体皮肤和蜂窝声学结构。 布置在声学皮肤和固体皮肤之间的细胞声学结构具有多个单元，每个单元具有布置在形成每个单元的一个或多个壁中的一个或多个排水孔。 该方法包括以下步骤：定义待切割的声学面板的一部分; 形成由声学皮肤封闭的切割区域; 通过声孔注入树脂; 在切割区域和声学皮肤上定位更换的蜂窝声学结构; 在替代的细胞声学结构上形成固体替代皮肤。

公开(公告)号：US20140086678A1

公开(公告)日：2014-03-27

申请号：US14093761

申请日：2013-12-02

Applicant: AIRCELLE

Inventor： Xavier CAZUC ,  Christophe Thorel ,  John Moutier

IPC: F04D29/52

CPC classification number: F04D29/52 ,  B64D29/00 ,  B64D29/06 ,  B64D2033/0286 ,  F02C7/04 ,  F05D2300/702 ,  F16B2200/50 ,  Y02T50/672

Abstract: An assembly for an aircraft nacelle includes a reinforcing plate and a flange that includes one first portion and one second portion. The first portion of the flange is attached to another flange, and the second portion extends transversely relative to the first portion and is attached onto a panel of the assembly. In particular, the reinforcing plate is attached directly, or optionally indirectly, onto the flange via an intermediate plate attached between the reinforcing plate and the flange. The reinforcing plate has a beveled portion opposite the second portion of the flange.

Abstract translation: 用于飞机机舱的组件包括加强板和包括一个第一部分和一个第二部分的凸缘。 凸缘的第一部分附接到另一凸缘，并且第二部分相对于第一部分横向延伸并且附接到组件的面板上。 特别地，加强板通过附接在加强板和凸缘之间的中间板直接地或可选地间接地附接到凸缘上。 加强板具有与凸缘的第二部分相对的斜面部分。

公开(公告)号：US20130315657A1

公开(公告)日：2013-11-28

申请号：US13671233

申请日：2012-11-07

Applicant: AIRCELLE

Inventor： Christophe Thorel ,  Bertrand Desjoyeaux ,  Florent Bouillon ,  John Moutier ,  Stéphane Bardin

IPC: F02C7/04

CPC classification number: F02C7/04 ,  B64D29/06 ,  F02C7/045 ,  F02K1/80 ,  F02K1/827 ,  Y02T50/672 ,  Y10T29/49826 ,  Y10T403/45

Abstract: A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule.

Abstract translation: 提供了一种用于飞机推进器的单元，其包括构造成附接到第二套圈的第一套圈和构造成固定到固定到第二套圈的第二对应连接凸缘的第一连接凸缘。 连接凸缘包括形成相对于第一套圈沿径向方向延伸的平面的部分。 第一套圈和对应的连接凸缘之间的连接偏移到与所述平面相对应的距离，该长度与用于阻尼通过第一套圈的力的通量产生的剪切产生弯曲力矩的长度相对应。