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公开(公告)号：US20130292202A1
公开(公告)日：2013-11-07
申请号：US13941044
申请日：2013-07-12
申请人： AIRCELLE
发明人： John MOUTIER , Emmanuel Anfray , Franck Maze , Herve Simon
CPC分类号： F02C7/24 , B29C73/04 , B29C73/26 , B64D2033/0206 , B64F5/40 , Y10T29/49398 , Y10T29/49618 , Y10T29/49732 , Y10T29/49734 , Y10T156/1082
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US20130261231A1
公开(公告)日：2013-10-03
申请号：US13901181
申请日：2013-05-23
申请人： AIRCELLE
发明人： Emmanuel Anfray , Franck Maze
IPC分类号： H05B1/02
CPC分类号： H05B1/0294 , B29C73/34
摘要： A method for heating a composite material area to be repaired includes placing a primary heating pad on the area to be repaired, and placing one or more satellite heating pads on the periphery of the primary pad in a manner that the satellite heating pads are adjacent to the edges of the primary pad.
摘要翻译： 一种用于加热要修复的复合材料区域的方法包括将主加热垫放置在待修复的区域上，并且以卫星加热垫相邻的方式将一个或多个卫星加热垫放置在主垫的周边上 主垫边缘。
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公开(公告)号：US08871839B2
公开(公告)日：2014-10-28
申请号：US13901181
申请日：2013-05-23
申请人： Aircelle
发明人： Emmanuel Anfray , Franck Maze
CPC分类号： H05B1/0294 , B29C73/34
摘要： A method for heating a composite material area to be repaired includes placing a primary heating pad on the area to be repaired, and placing one or more satellite heating pads on the periphery of the primary pad in a manner that the satellite heating pads are adjacent to the edges of the primary pad.
摘要翻译： 一种用于加热要修复的复合材料区域的方法包括将主加热垫放置在待修复的区域上，并且以卫星加热垫相邻的方式将一个或多个卫星加热垫放置在主垫的周边上 主垫的边缘。
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公开(公告)号：US08636107B2
公开(公告)日：2014-01-28
申请号：US13941044
申请日：2013-07-12
申请人： Aircelle
发明人： John Moutier , Emmanuel Anfray , Franck Maze , Herve Simon
CPC分类号： F02C7/24 , B29C73/04 , B29C73/26 , B64D2033/0206 , B64F5/40 , Y10T29/49398 , Y10T29/49618 , Y10T29/49732 , Y10T29/49734 , Y10T156/1082
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US20130062461A1
公开(公告)日：2013-03-14
申请号：US13662886
申请日：2012-10-29
申请人： Aircelle
CPC分类号： B64D29/06
摘要： A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame connected to each other and formed at least partly in composite materials. The half-structure includes a connecting hinge positioned in a junction area of the longitudinal beam and of the half-frame, the hinge being formed by composite materials laid out so that fibres of the composite materials are positioned in alignment with fibres of composite materials forming said front half-frame.
摘要翻译： 提供了一种用于飞机发动机机舱的支撑半结构，其包括至少一个纵向梁和彼此连接并且至少部分地形成复合材料的前半框架。 半结构包括位于纵向梁和半框架的接合区域中的连接铰链，铰链由复合材料形成，复合材料布置成使得复合材料的纤维与复合材料的纤维成对准 前半帧说
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