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1.发明授权Turbomachine rotor including at least one disk reinforced by a composite ring 有权涡轮机转子包括由复合环增强的至少一个盘公开(公告)号：US07334999B2
公开(公告)日：2008-02-26
申请号：US11427106
申请日：2006-06-28
申请人： Caroline Aumont , Sandrine Chatel , Bruno Jacques Gerard Dambrine , Didier Rene Andre Escure , Jean-Francois Fromentin , Jean-yves Guedou , Ludovic Edmond Camille Molliex , Stephane Rousselin
发明人： Caroline Aumont , Sandrine Chatel , Bruno Jacques Gerard Dambrine , Didier Rene Andre Escure , Jean-Francois Fromentin , Jean-yves Guedou , Ludovic Edmond Camille Molliex , Stephane Rousselin
IPC分类号： F01D5/02
CPC分类号： C22C49/00 , F01D5/282 , F04D29/023 , F04D29/321 , F05D2230/237 , F05D2300/133 , F05D2300/2112 , F05D2300/2261 , F05D2300/6032 , F05D2300/614
摘要： A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a groove in an enlarged portion of the disk and closing the groove by means of an annular plate after the ring has been put into place.
摘要翻译： 涡轮机转子，其包括至少一个具有环的盘，例如由金属包覆的碳化硅或氧化铝纱的卷绕构成的环。 根据本发明，复合环被接收在封闭的环形空腔中，例如， 通过在盘的扩大部分中加工凹槽并且在环已经就位之后通过环形板来闭合凹槽来限定。
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公开(公告)号：US20130017093A1
公开(公告)日：2013-01-17
申请号：US13517410
申请日：2010-12-20
摘要： An aircraft propeller blade including an airfoil-profile structure. The airfoil-profile structure includes at least one fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, and a shaping part made of cellular rigid material of determined shape, the reinforcement including at least two halves linked together by continuous weaving in the leading edge of the propeller blade, the two halves fitting tightly around the shaping part.
摘要翻译： 包括翼型轮廓结构的飞机螺旋桨叶片。 翼型轮廓结构包括通过三维编织纱线并由基体致密化的至少一种纤维增强材料和由确定形状的多孔刚性材料制成的成形部件，该加强件包括通过连续编织连接在一起的至少两个半部 在螺旋桨叶片的前缘中，两个半部紧密地配合在成形部件上。
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公开(公告)号：US5941688A
公开(公告)日：1999-08-24
申请号：US964632
申请日：1997-11-05
CPC分类号： F01D5/02 , F01D21/045 , Y02T50/672 , Y10T29/49316 , Y10T29/49327 , Y10T29/49336
摘要： A turbomachine rotor stage having a thin annular body comprising a metal alloy part reinforced by at least one fibrous ring which has a radial height h of at least 1.5 times its axial width l and which is embedded in the metal alloy part so that it projects radially outwardly from the inner wall thereof in order to stiffen the body and reduce the quantity of fibre material to be used.
摘要翻译： 一种涡轮机转子台，其具有薄的环形体，其包括由至少一个纤维环增强的金属合金部分，所述纤维环的径向高度h至少为其轴向宽度l的1.5倍，并且嵌入在金属合金部分中，使得其径向伸展 从其内壁向外侧，以便使主体变硬并减少待使用的纤维材料的数量。
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4.发明授权Method for manufacturing an integral rotationally symmetrical metal part including a reinforcement consisting of ceramic fibers 有权用于制造包括由陶瓷纤维组成的增强件的整体旋转对称金属部件的方法公开(公告)号：US09150948B2
公开(公告)日：2015-10-06
申请号：US14002538
申请日：2012-03-02
CPC分类号： C22C47/06 , B22F3/15 , C22C47/04 , C22C47/064 , Y10T29/49799 , Y10T29/49801
摘要： A method for manufacturing an integral rotationally symmetrical part, which includes producing a blank of the part around a cylindrical mandrel, the blank including at least one fibrous structure made of composite ceramic fibers coated with metal, followed by a diffusion-welding treatment of the blank by hot isostatic pressing, and optionally machining the thus-treated blank to obtain the part. The blank includes at least a first metal-wire layer between the mandrel and the composite fibrous structure, and at least a second metal-wire layer arranged around the composite fibrous structure to cover the composite fibrous structure.
摘要翻译： 一种用于制造整体旋转对称部分的方法，包括在圆筒形心轴周围产生该部分的坯料，该坯料包括由金属涂覆的复合陶瓷纤维制成的至少一个纤维结构，然后对该坯料进行扩散焊接处理 通过热等静压，并且可选地加工如此处理的坯料以获得部件。 所述坯料包括至少第一金属丝层，位于心轴和复合纤维结构之间，以及至少第二金属丝层，布置在复合纤维结构周围以覆盖复合纤维结构。
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5.发明授权Method of manufacturing a composite turbomachine blade, and a blade obtained by the method 有权复合涡轮机叶片的制造方法以及通过该方法得到的叶片公开(公告)号：US07581932B2
公开(公告)日：2009-09-01
申请号：US11550606
申请日：2006-10-18
IPC分类号： F01D5/14
CPC分类号： B29B11/16 , B29C70/24 , B29C70/48 , B29C70/541 , B29C70/543 , B29C70/545 , B29L2031/08 , F04D29/324 , F05D2240/303
摘要： The invention relates to a method of manufacturing a composite turbomachine blade, the method comprising the following steps: a) making a preform by three-dimensionally weaving yarns including tracer yarns disposed at least at the surface of the preform; b) cutting out said preform so as to leave intact a series of tracer yarns situated along a reference face of the preform; c) pre-deforming said cut-out preform; d) compacting and stiffening said pre-deformed preform; e) providing an injection mold in which said stiffened preform is placed; f) heating said injection mold; g) injecting a binder into said injection mold, the binder comprising a thermosettable resin; and h) extracting from the mold a composite molded part presenting substantially the shape and the dimensions of said blade. The invention is applicable to a making fan blade.
摘要翻译： 本发明涉及一种制造复合涡轮机叶片的方法，该方法包括以下步骤：a）通过三维编织纱线制造预成型件，所述纱线包括至少设置在预成型件表面的示踪纱线; b）切割所述预成型件，以便沿着预成型件的参考面定位一系列示踪纱线; c）对所述切割预制件进行预变形; d）压实和加固所述预变形预制件; e）提供其中放置所述加强预成型件的注射模具; f）加热注塑模具; g）将粘合剂注入所述注射模具中，所述粘合剂包含可热固树脂; 以及h）从所述模具中提取具有基本上所述刀片的形状和尺寸的复合模制部件。 本发明适用于制造风扇叶片。
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6.发明申请公开(公告)号：US20130333793A1
公开(公告)日：2013-12-19
申请号：US13980158
申请日：2012-01-09
IPC分类号： D03D13/00
CPC分类号： D03D13/00 , B29B11/16 , D03D11/00 , D03D13/004 , D03D25/005 , D10B2505/02
摘要： A reinforcing fiber structure woven as a single piece for fabricating a composite material part and including: first and second fiber substructures, each fiber substructure including at least one independent portion obtained by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns that are independent from the other substructure; and an assembly portion between the least first and second fiber substructures in which a plurality of adjacent layers of warp yarns of the first fiber substructure are interlinked by at least some of the warp yarns of the second fiber substructure.
摘要翻译： 一种用于制造复合材料部件而编织为单件的增强纤维结构，包括：第一和第二纤维亚结构，每个纤维子结构包括通过在多层经纱层和多层之间的多层织造获得的至少一个独立部分 的纬纱独立于其他子结构; 以及所述最小第一和第二纤维子结构之间的组合部分，其中所述第一纤维子结构的多个相邻的经纱层由所述第二纤维子结构的至少一些经纱相互连接。
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公开(公告)号：US20130319067A1
公开(公告)日：2013-12-05
申请号：US14000609
申请日：2012-02-24
CPC分类号： B23P15/04 , B22F3/15 , B22F5/04 , B23K20/021 , B23P15/02 , B29D99/0025 , B29D99/0028 , C22C47/04 , C22C47/064 , F04D29/324 , F05D2240/303
摘要： A method for manufacturing a metal part by producing a preform with a fibrous structure of metal fibers, and subjecting the preform to hot isostatic pressing in a tool until a solid part is obtained, the tool including at least one first element including a cavity for molding the part. The first tool element is elongate in a direction between two ends, and the fibrous structure is at least partially formed by winding at least one metal wire around the first tool element in the direction, from one end to the other. The method can be used, for example, for manufacturing reinforcement parts for a fan blade of a turbojet engine.
摘要翻译： 一种通过制造具有金属纤维的纤维结构的预成型件来制造金属部件的方法，并且使预制件在工具中进行热等静压，直到获得固体部分，该工具包括至少一个第一元件，第一元件包括用于模制的空腔 那个部分。 第一工具元件在两个端部之间的方向上是细长的，并且纤维结构至少部分地通过在从一端到另一端的方向上缠绕第一工具元件的至少一个金属丝而形成。 该方法可用于例如用于制造涡轮喷气发动机的风扇叶片的增强部件。
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8.发明授权Method for manufacturing a one-piece annular metal part having a reinforcing insert of composite material 有权用于制造具有复合材料的加强插入物的单件环形金属部件的方法公开(公告)号：US08448837B2
公开(公告)日：2013-05-28
申请号：US13346014
申请日：2012-01-09
IPC分类号： B23K31/02
CPC分类号： C22C47/04 , B22F3/15 , B22F5/009 , C22C47/066 , Y10T29/49318
摘要： A method for manufacturing a one-piece annular metal part having a reinforcing insert of composite material includes forming a blank of the part by superimposing, around a rotating cylindrical mandrel, layers of metal wire and layers of coated fiber, the layers of coated composite fiber being arranged in the blank according to the positioning of the insert in the part; placing the blank in a receiving tool, and applying a hot isostatic pressing treatment to the blank; and extracting the treated blank from the receiving tool and, as required, machining the treated blank to obtain the one-piece annular metal part having a reinforcing insert.
摘要翻译： 用于制造具有复合材料的加强插入件的一体式环形金属部件的方法包括通过在旋转的圆柱形心轴周围叠加金属丝和涂覆纤维层来形成部件的坯件，涂覆的复合纤维层 根据插入件在零件中的位置布置在坯件中; 将坯料放置在接收工具中，并对坯料进行热等静压处理; 并从接收工具中提取经处理的坯料，并根据需要对经处理的坯料进行加工，以获得具有加强插入件的一体式环形金属部件。
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公开(公告)号：US07926761B2
公开(公告)日：2011-04-19
申请号：US11425082
申请日：2006-06-19
申请人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Fabienne Lacorre , Alain Madec , Jean-Noel Mahieu
发明人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Fabienne Lacorre , Alain Madec , Jean-Noel Mahieu
CPC分类号： D03D25/005 , B29C70/24 , B29C70/48 , B29L2031/3076 , B29L2031/7488 , B64C25/12 , F16C7/026 , F16C2326/43 , Y10T74/2142 , Y10T442/3195 , Y10T442/3203 , Y10T442/3211
摘要： The invention provides a mechanical part for hinging to other mechanical parts at its ends, the mechanical part being made at least in part out of composite material from a central fiber preform and a peripheral fiber preform both of three-dimensional woven fabric, which preforms are assembled together while dry and then impregnated with resin, the peripheral preform surrounding the central preform in such a manner as to leave two empty spaces at the ends of the part and between the two preforms, which spaces are dedicated to hinging to said other parts. Metal inserts can be received in said spaces. The mechanical part can be used as a lever for a landing gear brace.
摘要翻译： 本发明提供了一种用于在其端部铰接到其它机械部件的机械部件，所述机械部件至少部分地由复合材料制成，所述复合材料来自中心纤维预制件和外部纤维预制件，所述三维机织织物是预制件 组装在一起，同时干燥，然后用树脂浸渍，周围预型件围绕中央预制件，以便在部件的端部和两个预制件之间留下两个空的空间，这些空间用于铰接到所述其它部件。 金属插件可以在所述空间中接收。 机械部件可用作起落架支架的杠杆。
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公开(公告)号：US10180069B2
公开(公告)日：2019-01-15
申请号：US13575170
申请日：2011-01-20
摘要： A turbine engine blade made of composite material including fiber reinforcement obtained by weaving a first plurality of yarns with a second plurality of yarns, the yarns of the first plurality of yarns being arranged in successive layers and extending in a longitudinal direction of the fiber blank corresponding to a longitudinal direction of the blade, the reinforcement being densified by a matrix. The blade includes one or more internal channels extending in the longitudinal direction of the blade.
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