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1.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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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：US09162750B2
公开(公告)日：2015-10-20
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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4.发明申请METHOD OF FABRICATING A COMPOSITE MATERIAL BLADE HAVING INTERNAL CHANNELS, AND A COMPOSITE MATERIAL TURBINE ENGINE BLADE 审中-公开制作具有内部通道的复合材料叶片的方法和复合材料涡轮发动机叶片公开(公告)号：US20130017094A1
公开(公告)日：2013-01-17
申请号：US13575170
申请日：2011-01-20
CPC分类号： F01D5/282 , B29C33/52 , B29C70/24 , B29C70/48 , B29D99/0025 , B29L2031/08 , D03D25/005 , F01D5/187 , F05D2260/20 , F05D2300/21 , F05D2300/224 , Y10T29/49337
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.
摘要翻译： 一种由复合材料制成的涡轮发动机叶片，包括通过用第二多根纱线编织第一多根纱线而获得的纤维增强件，所述第一多根纱线的纱线沿连续层布置并且在纤维坯料的纵向方向上相对延伸 相对于叶片的纵向方向，加强物被矩阵致密化。 叶片包括在叶片的纵向方向上延伸的一个或多个内部通道。
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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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7.发明授权Method of manufacturing a gas turbine casing out of composite material, and a casing as obtained thereby 有权从复合材料制造燃气轮机壳体的方法以及由此获得的壳体公开(公告)号：US08322971B2
公开(公告)日：2012-12-04
申请号：US12033624
申请日：2008-02-19
申请人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
发明人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , B29C70/24 , B29C70/443 , F05D2240/11 , F05D2300/603 , Y02T50/672
摘要： A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.
摘要翻译： 特别是用于燃气轮机风扇的不同厚度的复合材料壳体通过形成纤维增强物并用基体致密化而制成。 纤维增强件通过将纤维织构的叠层卷绕到心轴上而形成，该纹理由具有变化厚度的三维编织制成。
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8.发明申请METHOD OF MANUFACTURING A GAS TURBINE CASING OUT OF COMPOSITE MATERIAL, AND A CASING AS OBTAINED THEREBY 有权制造复合材料的气体涡轮机的方法及其获得的试验公开(公告)号：US20080206048A1
公开(公告)日：2008-08-28
申请号：US12033624
申请日：2008-02-19
申请人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
发明人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
CPC分类号： F01D21/045 , B29C70/24 , B29C70/443 , F05D2240/11 , F05D2300/603 , Y02T50/672
摘要： A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.
摘要翻译： 特别是用于燃气轮机风扇的不同厚度的复合材料壳体通过形成纤维增强物并用基体致密化而制成。 纤维增强件通过将纤维织构的叠层卷绕到心轴上而形成，该纹理由具有变化厚度的三维编织制成。
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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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10.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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