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公开(公告)号：US20150314553A1
公开(公告)日：2015-11-05
申请号：US14796490
申请日：2015-07-10
申请人： AIRCELLE
CPC分类号： B32B3/266 , B29B11/16 , B29C70/22 , B29C70/30 , B29C70/887 , B29C2793/0045 , B29L2031/06 , B32B37/18 , B32B2305/08 , B32B2305/188 , Y10T156/10 , Y10T428/24322
摘要： A structural component is made of composite material, including at least one assembly orifice, the component being composed of a stack of plies of fibers which include at least one layer of plies of regular fibers and at least one reinforcing ply. The reinforcing ply is composed of a woven composite textile preform formed by a weave obtained by assembling a plurality of circumferential warp fibers that form a path around the assembly orifice and weft fibers that extend radially with respect to the center of the orifice.
摘要翻译： 结构部件由复合材料制成，包括至少一个组装孔口，该部件由一叠纤维层组成，包括至少一层普通纤维层和至少一层增强层。 增强层由编织复合纺织品预成型件组成，织物预制件通过组装多个周向经纱而形成，所述编织形成围绕组装孔的路径和相对于孔的中心径向延伸的纬纱。
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公开(公告)号：US20140026974A1
公开(公告)日：2014-01-30
申请号：US13953368
申请日：2013-07-29
申请人： AIRCELLE
CPC分类号： B29D99/001 , B29C70/48 , B29C70/84 , B29L2031/087 , B29L2031/7504 , B64D29/00 , B64D33/02 , F02C7/04 , Y10T137/0536
摘要： A method for manufacturing a nacelle air intake lip including a plurality of components includes the following steps. The first step is positioning, inside a mold, two components within a set of fibrous layers encompassing all or part of the components so that a preform is formed. Next step is performing impregnation of the obtained preform to obtain molding of the nacelle air intake lip.
摘要翻译： 包括多个部件的制造机舱进气口的方法包括以下步骤。 第一步是在模具内部定位一组包含全部或部分组件的纤维层中的两个部件，从而形成预制件。 下一步是对获得的预制件进行浸渍以获得机舱进气口的模制。
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3.发明申请METHOD FOR MANUFACTURING A STRUCTURE WITH CELLULAR CORES FOR A TURBOJET NACELLE 有权用于制造用于涡轮喷射器的细孔结构的方法公开(公告)号：US20150267613A1
公开(公告)日：2015-09-24
申请号：US14635667
申请日：2015-03-02
申请人： AIRCELLE
CPC分类号： 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
摘要： 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.
摘要翻译： 本公开涉及一种用于制造具有多孔芯的结构的方法，所述结构可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。
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4.发明申请METHOD FOR MANUFACTURING COMPOSITE PARTS, MANUFACTURING FACILITY IMPLEMENTING SUCH A METHOD, AND COMPOSITE PARTS MANUFACTURED THEREBY 审中-公开制造复合材料部件的方法，实施这种方法的制造设备以及制造的复合材料部件公开(公告)号：US20150174833A1
公开(公告)日：2015-06-25
申请号：US14638386
申请日：2015-03-04
申请人： Aircelle
发明人： Bertrand DESJOYEAUX
CPC分类号： B29C70/40 , B29B11/16 , B29C67/0018 , B29C70/021 , B29C70/222 , B29C70/30 , B29K2105/258 , B29L2023/00 , B29L2031/772
摘要： The present disclosure relates to a method for manufacturing composite parts and to manufacturing equipment. The present disclosure is useful in the field of aircraft construction. During a first phase, the part is designed, the geometry is computed, and the fabric architecture of the fabric preform and a mandrel for forming the first state of the preform are calculated. During a second phase, the preform fabric and the mandrel are produced. During a third phase, the mandrel is wrapped with the fabric, the preform is extracted from the mandrel in order to collapse a portion of the preform, and the preform is impregnated in order to obtain the desired part.
摘要翻译： 本公开涉及一种用于制造复合部件和制造设备的方法。 本公开在飞机制造领域是有用的。 在第一阶段期间，对零件进行设计，计算出几何形状，并计算织物预制件的织物结构和用于形成预制件的第一状态的芯棒。 在第二阶段期间，制造预成型织物和心轴。 在第三阶段期间，心轴与织物一起包裹，预制件从心轴中抽出以折叠预制件的一部分，并且浸渍预成型件以获得所需的部分。
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5.发明申请METHOD FOR MANUFACTURING AN AIR INTAKE STRUCTURE FOR A TURBOJET ENGINE NACELLE 有权用于制造涡轮发动机空气吸入结构的方法公开(公告)号：US20130312263A1
公开(公告)日：2013-11-28
申请号：US13958246
申请日：2013-08-02
申请人： Aircelle
IPC分类号： B23P15/00
CPC分类号： B23P15/008 , B29C70/44 , B29C70/48 , B29C70/84 , B64D33/02 , B64D2033/0286 , Y10T29/49346
摘要： A method for manufacturing an air-intake structure for a turbojet-engine nacelle includes two component parts, i.e. one air-intake lip structure and one outer cowl for the air-intake structure. In particular, the method includes the following steps: separately manufacturing the component parts such that each integrates one overlapping portion with a part to which is to be attached. The overlapping portion is configured such that an outer surface of the outer overlapping portion provides continuity with an outer surface of the outer cowl associated with the inner overlapping portion. To secure the overlapping portions, glue or a fastener may be used.
摘要翻译： 用于制造涡轮喷气发动机机舱的进气结构的方法包括两个部件，即一个进气口结构和一个用于进气结构的外罩。 特别地，该方法包括以下步骤：分开制造组成部件，使得每个部件将一个重叠部分与要附接的部分集成。 重叠部分构造成使得外部重叠部分的外表面与外部整流罩的与内部重叠部分相关联的外表面提供连续性。 为了固定重叠部分，可以使用胶水或紧固件。
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公开(公告)号：US20130108432A1
公开(公告)日：2013-05-02
申请号：US13718562
申请日：2012-12-18
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D5/282 , F01D5/34 , F01D9/04 , F01D25/24 , F02C7/04 , F02C7/20 , F02K3/06 , F05D2240/14 , F05D2250/51 , F05D2300/603 , Y02T50/672
摘要： An airflow-straightening structure for an aircraft engine is provided that includes a hoop inside which there are arranged a plurality of flow-straightening vanes bearing a hub of a fan. Also includes is a clevis for connecting to a suspension strut, the clevis being fixed to said hoop. The structure has at least two elements chosen from the group of the hoop, the plurality of vanes, the hub and the clevis, which are formed in one piece, that is to say without any assembly operation. Additionally, at least one of the elements chosen from the group is at least partially formed of a composite material.
摘要翻译： 提供了一种用于飞行器发动机的气流矫直结构，其包括箍，其内布置有多个带有风扇毂的流动整流叶片。 还包括用于连接到悬架支柱的U形夹，U形夹固定到所述箍。 该结构具有至少两个元件，其选自环形组，多个叶片，轮毂和U形夹组，其形成为一体，也就是说没有任何组装操作。 另外，从组中选择的至少一个元素至少部分地由复合材料形成。
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7.发明申请WOVEN PREFORM FOR PRODUCING A CIRCUMFERENTIAL OR TOROIDAL REINFORCEMENT HAVING AN OMEGA-SHAPED CROSS-SECTION 审中-公开用于生产具有欧米茄形横截面的圆形或多边形加固的WOVEN预制公开(公告)号：US20160376735A1
公开(公告)日：2016-12-29
申请号：US15262029
申请日：2016-09-12
申请人： AIRCELLE
CPC分类号： D03D25/005 , B29B11/16 , D03D1/00 , D03D11/02 , D03D13/002 , D03D49/20 , D10B2403/023 , D10B2505/02 , D10B2505/12
摘要： The disclosure relates to a shape-woven preform which has an omega-shaped cross-section including a core and a sole. At least one part of the core and at least one part of the sole have weft yarns in common with one another.
摘要翻译： 本公开涉及一种具有包括芯和鞋底的Ω形横截面的形状编织预制件。 芯的至少一部分和鞋底的至少一部分具有相互共同的纬纱。
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8.发明申请FIBER STRUCTURE FOR AN AXISYMMETRIC COMPONENT MADE OF COMPOSITE MATERIAL WITH A VARYING DIAMETER, AND COMPONENT COMPRISING SAME 有权具有变化直径的复合材料的轴对称组分的纤维结构和包含其的组分公开(公告)号：US20150354103A1
公开(公告)日：2015-12-10
申请号：US14761792
申请日：2014-01-09
CPC分类号： B29B11/16 , B60B11/06 , B60B2310/241 , B60B2360/3444 , B60Y2200/51 , D03D3/02 , D03D25/005 , D10B2101/06 , D10B2101/08 , D10B2505/02 , Y10T428/1314 , Y10T428/1362
摘要： A single-piece woven fiber structure for fabricating an axisymmetric part of varying diameter made out of composite material, the fiber structure having a portion of frustoconical shape with a large diameter and a small diameter, the ratio between the large diameter and the small diameter being not less than 2. The fiber structure is formed by winding layers of warp and weft yarns that are woven on a mandrel having a profile that is defined as a function of the profile of the part to be fabricated with warp yarn take-up. For each layer of yarns, the weft yarns are angularly distributed on a single diameter in a zone of the large diameter of the portion of frustoconical shape and on at least two different diameters in a zone of the small diameter of the portion of frustoconical shape in order to form at least two superposed plies of weft yarns.
摘要翻译： 一种用于制造由复合材料制成的不同直径的轴对称部分的单件编织纤维结构，所述纤维结构具有具有大直径和小直径的截头圆锥形形状的一部分，大直径和小直径之间的比率 不小于2.纤维结构通过卷绕经纱和纬纱的层而形成，该纬纱和纬纱在具有轮廓的心轴上编织，该轮廓被定义为待经纱卷绕的待制造部件的轮廓的函数。 对于每层纱线，纬纱在截头圆锥形部分的大直径区域中的单个直径上成角度分布，并且在截头圆锥形状部分的小直径区域中的至少两个不同直径上 以形成至少两个重叠的纬纱层。
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公开(公告)号：US20130121814A1
公开(公告)日：2013-05-16
申请号：US13731150
申请日：2012-12-31
IPC分类号： F01D25/24
摘要： A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.
摘要翻译： 提供了一种用于涡轮喷气发动机的机舱，其包括涡轮喷气发动机上游的进气口，旨在围绕涡轮喷气发动机及其壳体的风扇的中间部分和下游部分。 中间部分由能够确保机舱的外部空气动力学连续性的至少一个航空结构制成，并且航空结构刚性地结合，以便能够被分离到至少一个周围的固定结构。
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