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1.发明授权Composite material turbomachine engine blade or vane, compressor stator segment or turbine nozzle segment incorporating such vanes and method for manufacturing same 有权复合材料涡轮机发动机叶片或叶片，压缩机定子段或包含这种叶片的涡轮喷嘴段及其制造方法公开(公告)号：US09062562B2
公开(公告)日：2015-06-23
申请号：US13607341
申请日：2012-09-07
申请人： Dominique Coupe , Clement Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon , Antoine Jean-Philippe Beaujard , Elric Georges Andre Fremont
发明人： Dominique Coupe , Clement Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon , Antoine Jean-Philippe Beaujard , Elric Georges Andre Fremont
CPC分类号： F01D25/00 , D03D25/005 , F01D5/00 , F01D5/282 , F01D9/02 , F05D2300/603 , Y10T29/4932
摘要： A method for fabricating a turbomachine blade or vane of composite material including fiber reinforcement densified by a matrix is disclosed. The method includes: making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a blade platform preform; and densifying the preform with a matrix to obtain a composite material blade or vane having fiber reinforcement constituted by the preform and densified by the matrix, forming a single part with at least one incorporated platform.
摘要翻译： 公开了一种用于制造复合材料的涡轮机叶片或叶片的方法，包括由基体致密化的纤维增强材料。 该方法包括：通过三维织造制成单件纤维坯料; 成形纤维毛坯以获得具有形成刀片翼型和根部预制件的第一部分和形成刀片平台预制件的至少一个第二部分的单件式纤维预制件; 并用基体致密化预型件，以获得具有纤维增强材料的复合材料叶片或叶片，该纤维增强材料由预型体构成，并由基体致密化，由至少一个结合的平台形成单一部分。
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2.发明申请TURBINE ENGINE BLADE OR VANE MADE OF COMPOSITE MATERIAL, TURBINE NOZZLE OR COMPRESSOR STATOR INCORPORATING SUCH VANES AND METHOD OF FABRICATING SAME 有权涡轮发动机叶片或复合材料的风扇，涡轮喷嘴或压缩机定子及其制造方法及其制造方法公开(公告)号：US20140030076A1
公开(公告)日：2014-01-30
申请号：US13607371
申请日：2012-09-07
申请人： ROMAIN NUNEZ , Stephane Blanchard , Guillaume Renon , Dominique Coupe , Clement Roussille , Antoine Jean-Philippe Beaujard , Elric Georges Andre Fremont
发明人： ROMAIN NUNEZ , Stephane Blanchard , Guillaume Renon , Dominique Coupe , Clement Roussille , Antoine Jean-Philippe Beaujard , Elric Georges Andre Fremont
IPC分类号： F01D5/28
CPC分类号： F01D5/282 , B29C70/222 , B29L2031/08 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B35/806 , C04B37/006 , C04B37/008 , C04B2235/483 , C04B2235/5244 , C04B2235/5256 , C04B2235/612 , C04B2235/614 , C04B2237/123 , C04B2237/127 , C04B2237/128 , C04B2237/365 , C04B2237/38 , D03D25/005 , F01D5/284 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/49336
摘要： A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.
摘要翻译： 用于制造由复合材料制成的涡轮发动机叶片或叶片的方法包括：执行三维织造以制造单件纤维坯料; 成形纤维毛坯以获得具有形成用于至少叶片/叶片翼型件的预成型件的第一部分的单件式纤维预制件，形成用于叶片/叶片内平台的内部的预制件的至少一个第二部分或用于 叶片/叶片外平台的外部部分和至少一个第三部分，形成用于叶片/叶片内平台的外部部分或叶片/叶片外部平台的内部部分的预制件; 并用基质致密化纤维预成型件以获得复合材料刀片，并且形成具有并入其中的内平台和/或外平台的单件。
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3.发明授权Turbine engine blade or vane made of composite material, turbine nozzle or compressor stator incorporating such vanes and method of fabricating same 有权由复合材料制成的涡轮发动机叶片或叶片，包含这种叶片的涡轮喷嘴或压缩机定子及其制造方法公开(公告)号：US09506355B2
公开(公告)日：2016-11-29
申请号：US13607371
申请日：2012-09-07
申请人： Romain Nunez , Stephane Blanchard , Guillaume Renon , Dominique Coupe , Clement Roussille , Antoine Jean-Philippe Beaujard , Elric Georges Andre Fremont
发明人： Romain Nunez , Stephane Blanchard , Guillaume Renon , Dominique Coupe , Clement Roussille , Antoine Jean-Philippe Beaujard , Elric Georges Andre Fremont
IPC分类号： F01D5/28 , B29C70/22 , C04B35/571 , C04B35/628 , C04B35/80 , C04B37/00 , B29L31/08
CPC分类号： F01D5/282 , B29C70/222 , B29L2031/08 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B35/806 , C04B37/006 , C04B37/008 , C04B2235/483 , C04B2235/5244 , C04B2235/5256 , C04B2235/612 , C04B2235/614 , C04B2237/123 , C04B2237/127 , C04B2237/128 , C04B2237/365 , C04B2237/38 , D03D25/005 , F01D5/284 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/49336
摘要： A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.
摘要翻译： 用于制造由复合材料制成的涡轮发动机叶片或叶片的方法包括：执行三维织造以制造单件纤维坯料; 成形纤维毛坯以获得具有形成用于至少叶片/叶片翼型件的预成型件的第一部分的单件式纤维预制件，形成用于叶片/叶片内平台的内部的预制件的至少一个第二部分或用于 叶片/叶片外平台的外部部分和至少一个第三部分，形成用于叶片/叶片内平台的外部部分或叶片/叶片外部平台的内部部分的预制件; 并用基质致密化纤维预成型件以获得复合材料刀片，并且形成具有并入其中的内平台和/或外平台的单件。
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4.发明授权公开(公告)号：US09080454B2
公开(公告)日：2015-07-14
申请号：US13131285
申请日：2009-11-26
申请人： Dominique Coupe , Clément Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon
发明人： Dominique Coupe , Clément Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon
IPC分类号： F01D25/00 , F01D5/28 , B29C70/22 , B29C70/24 , D03D25/00 , C04B35/571 , C04B35/628 , B29L31/08
CPC分类号： F01D5/282 , B29B11/16 , B29C70/222 , B29C70/24 , B29L2031/08 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B2235/5244 , C04B2235/5256 , C04B2235/616 , D03D25/005 , F05D2300/21 , F05D2300/6033 , F05D2300/614 , F05D2300/702 , Y02T50/67 , Y02T50/672
摘要： A method of fabricating a turbomachine blade out of a composite material including fiber reinforcement densified by a matrix, the method including making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a preform for an inner or outer blade platform; and densifying the preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, forming a single part with incorporated inner and/or outer platform.
摘要翻译： 一种由包括由基体致密化的纤维增强材料的复合材料制造涡轮机叶片的方法，该方法包括通过三维编织制造单件纤维坯料; 成形纤维毛坯以获得具有形成叶片翼型和根部预制件的第一部分和形成用于内部或外部叶片平台的预制件的至少一个第二部分的单件式纤维预制件; 并用基质致密预成型件，以获得具有由预成型件构成的纤维增强材料并由基体致密化的复合材料刀片，形成具有并入的内部和/或外部平台的单个部件。
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5.发明申请公开(公告)号：US20110311368A1
公开(公告)日：2011-12-22
申请号：US13131285
申请日：2009-11-26
申请人： Dominique Coupe , Clément Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon
发明人： Dominique Coupe , Clément Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon
IPC分类号： F01D5/14
CPC分类号： F01D5/282 , B29B11/16 , B29C70/222 , B29C70/24 , B29L2031/08 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B2235/5244 , C04B2235/5256 , C04B2235/616 , D03D25/005 , F05D2300/21 , F05D2300/6033 , F05D2300/614 , F05D2300/702 , Y02T50/67 , Y02T50/672
摘要： A method of fabricating a turbomachine blade out of a composite material including fiber reinforcement densified by a matrix, the method including making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a preform for an inner or outer blade platform; and densifying the preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, fowling a single part with incorporated inner and/or outer platform.
摘要翻译： 一种由包括由基体致密化的纤维增强材料的复合材料制造涡轮机叶片的方法，该方法包括通过三维编织制造单件纤维坯料; 成形纤维毛坯以获得具有形成叶片翼型和根部预制件的第一部分和形成用于内部或外部叶片平台的预制件的至少一个第二部分的单件式纤维预制件; 并用矩阵致密化预成型件，以获得具有纤维增强材料的复合材料刀片，该纤维增强材料由预成型件构成并由基体致密化，使单个部件与内部和/或外部平台结合在一起。
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公开(公告)号：US09605543B2
公开(公告)日：2017-03-28
申请号：US13515879
申请日：2010-12-10
IPC分类号： F01D5/14 , C04B35/571 , C04B35/628 , C04B35/80 , D03D11/02 , D03D25/00 , F01D5/28 , B23P15/04 , B29B11/16
CPC分类号： F01D5/147 , B23P15/04 , B29B11/16 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62897 , C04B35/806 , C04B2235/5244 , C04B2235/5252 , C04B2235/614 , C04B2235/616 , D03D11/02 , D03D25/005 , F01D5/282 , F05D2300/6012 , F05D2300/603 , F05D2300/614 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10T29/49337
摘要： A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.
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7.发明申请TURBINE ENGINE BLADE MADE OF COMPOSITE MATERIAL, AND A METHOD OF FABRICATING IT 有权复合材料涡轮发动机叶片及其制造方法公开(公告)号：US20130089429A1
公开(公告)日：2013-04-11
申请号：US13515879
申请日：2010-12-10
CPC分类号： F01D5/147 , B23P15/04 , B29B11/16 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62897 , C04B35/806 , C04B2235/5244 , C04B2235/5252 , C04B2235/614 , C04B2235/616 , D03D11/02 , D03D25/005 , F01D5/282 , F05D2300/6012 , F05D2300/603 , F05D2300/614 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10T29/49337
摘要： A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.
摘要翻译： 由包括由基体致密化的纤维增强材料的复合材料制成的涡轮发动机叶片通过以下方法制造：包括：进行三维织造以制造单片纤维坯料; 成形纤维坯料以获得单片纤维预制件，其具有形成用于叶根和翼型的预成型件的第一部分，形成用于叶片内平台的预成型件或叶片外平台的擦拭器的至少一个第二部分，以及 至少一个第三部分形成用于加强叶片内平台或用于叶片外平台的悬突的预制件; 并用基体致密化纤维预成型体，得到具有由预成型体构成的纤维增强材料并由基体致密化的复合材料刀片，并且形成一个内部和/或外部平台的单件。
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公开(公告)号：US08846147B2
公开(公告)日：2014-09-30
申请号：US13131320
申请日：2009-11-26
IPC分类号： C23C16/00 , C04B35/565 , F01D17/20 , C04B35/83 , C04B35/628 , C04B35/80 , F01D5/28 , B29B11/16 , C04B35/52 , B05D3/12 , B29B11/02
CPC分类号： B29B11/16 , B29B11/02 , C04B35/52 , C04B35/565 , C04B35/6286 , C04B35/62868 , C04B35/62873 , C04B35/62897 , C04B35/806 , C04B35/83 , C04B2235/5244 , C04B2235/5252 , C04B2235/614 , C04B2235/94 , D03D25/005 , F01D5/282 , F01D17/20 , F05D2300/601 , F05D2300/6012 , F05D2300/614 , Y02T50/672 , Y10S427/10
摘要： A method of fabricating a complex part out of composite material including three-dimensional woven fiber reinforcement densified by a matrix, the method including three-dimensionally weaving a continuous fiber strip including a succession of fiber blanks for preforms of a plurality of parts that are to be fabricated; subsequently cutting individual fiber blanks out from the strip, each blank being a one-piece blank; shaping a cut-out blank to obtain a one-piece fiber preform having a shape that is close to the shape of a part that is to be fabricated; consolidating the preform in the desired shape; and densifying the consolidated preform by forming a matrix by chemical vapor infiltration.
摘要翻译： 一种由复合材料制成复合材料的方法，包括由基体致密化的三维编织纤维增强材料，该方法包括三维编织连续的纤维条，该连续纤维条包括一系列纤维毛坯，用于多个零件的预制件 被制造 随后从条带中切割出单根纤维毛坯，每个坯料为一片坯料; 成形切割坯料以获得具有接近要制造的部件的形状的形状的一体式纤维预制件; 将预成型件固结成所需的形状; 并通过化学气相渗透形成基质来致密化固结的预成型体。
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公开(公告)号：US20110293828A1
公开(公告)日：2011-12-01
申请号：US13131320
申请日：2009-11-26
IPC分类号： C23C16/02
CPC分类号： B29B11/16 , B29B11/02 , C04B35/52 , C04B35/565 , C04B35/6286 , C04B35/62868 , C04B35/62873 , C04B35/62897 , C04B35/806 , C04B35/83 , C04B2235/5244 , C04B2235/5252 , C04B2235/614 , C04B2235/94 , D03D25/005 , F01D5/282 , F01D17/20 , F05D2300/601 , F05D2300/6012 , F05D2300/614 , Y02T50/672 , Y10S427/10
摘要： A method of fabricating a complex part out of composite material including three-dimensional woven fiber reinforcement densified by a matrix, the method including three-dimensionally weaving a continuous fiber strip including a succession of fiber blanks for preforms of a plurality of parts that are to be fabricated; subsequently cutting individual fiber blanks out from the strip, each blank being a one-piece blank; shaping a cut-out blank to obtain a one-piece fiber preform having a shape that is close to the shape of a part that is to be fabricated; consolidating the preform in the desired shape; and densifying the consolidated preform by forming a matrix by chemical vapor infiltration.
摘要翻译： 一种由复合材料制成复合材料的方法，包括由基体致密化的三维编织纤维增强材料，该方法包括三维编织连续的纤维条，该连续纤维条包括一系列纤维毛坯，用于多个零件的预制件 被制造 随后从条带中切割出单根纤维毛坯，每个坯料为一片坯料; 成形切割坯料以获得具有接近要制造的部件的形状的形状的一体式纤维预制件; 将预成型件固结成所需的形状; 并通过化学气相渗透形成基质来致密化固结的预成型体。
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公开(公告)号：US20120055609A1
公开(公告)日：2012-03-08
申请号：US13263176
申请日：2010-03-26
申请人： Stephane Pierre Guillaume Blanchard , Eric Bouillon , Dominique Coupe , Hubert Illand , Clement Roussille
发明人： Stephane Pierre Guillaume Blanchard , Eric Bouillon , Dominique Coupe , Hubert Illand , Clement Roussille
CPC分类号： C04B35/64 , B29B11/16 , B29C70/24 , B29D99/0025 , B29L2031/08 , C04B35/524 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62897 , C04B35/806 , C04B2235/5244 , C04B2235/5252 , C04B2235/5256 , C04B2235/616 , D03D25/005 , F01D5/282 , Y02T50/672 , Y10T29/49321 , Y10T29/49325
摘要： A method of fabricating a composite-material turbomachine blade having platform incorporated therein includes separately making a blade platform element that comprises rigidified fiber reinforcement and that has a shape close to that of a platform of the blade to be fabricated, with at least one opening being formed through the platform element. The opening has the shape of the profile of the airfoil of the blade to be fabricated. Three-dimensional weaving is used to make a flexible fiber blank as a single piece that includes blade airfoil-and-root preform portions. The platform element is engaged, via its opening, on the flexible fiber blank while deforming it so as to assemble the platform element with the fiber blank. The fiber blank is shaped together with the platform element assembled thereon to obtain a blade preform of a shape that is close to the shape of the blade to be fabricated. After shaping, the blade preform is consolidated in its shape in a shaper. Additionally, final densification of the consolidated blade preform is performed in order to obtain a composite-material blade having an incorporated platform.
摘要翻译： 制造具有并入其中的平台的复合材料涡轮机叶片的方法包括分别制造包括刚性纤维增强件并且具有接近待制造的叶片的平台的形状的叶片平台元件，其中至少一个开口 通过平台元件形成。 开口具有要制造的叶片的翼型的形状。 使用三维编织将柔性纤维坯料制成包括叶片翼型和根部预制件部分的单件。 平台元件通过其开口接合在柔性纤维坯料上，同时变形，以便将平台元件与纤维坯料组装。 纤维坯料与组装在其上的平台元件一起成形，以获得接近待制造的刀片形状的形状的刀片预制件。 在成形之后，刀片预成型件以整形器固结成其形状。 此外，为了获得具有并入的平台的复合材料刀片，进行固结刀片预成型件的最终致密化。
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