Patents by Inventor Matthieu Gimat
Matthieu Gimat has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11072100Abstract: The invention relates to a compaction assembly comprising a shaping mold (24) delimiting an upwardly open housing, capable of receiving a woven preform cut out beforehand (10a), and a vertically moveable compaction tool (128) and forming, with the shaping mold, (24), a compaction assembly for the preform placed beforehand in the housing. The compaction tool (128) includes at least one foot portion (128A). The compaction tool (128) comprises at least three separate compaction blocks (1281-1287). Application to the manufacturing of composite fan blades for a turbomachine.Type: GrantFiled: October 3, 2014Date of Patent: July 27, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Yann Marchal, Jeremy Engel, Matthieu Gimat
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Patent number: 10781708Abstract: A composite material guide vane for a gas turbine engine, the composite material including fiber reinforcement densified by a matrix, the fiber reinforcement being formed as a single piece by three-dimensional weaving and including an airfoil and at least two fastener flanges extending from a radial end of the vane towards opposite side faces of the airfoil, the fastener flanges being axially offset from each other.Type: GrantFiled: August 18, 2015Date of Patent: September 22, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Gimat, François Charleux, Sébastien Marin, Gwenael Marion
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Patent number: 10724159Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.Type: GrantFiled: September 21, 2018Date of Patent: July 28, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Yann Marchal, Matthieu Gimat, Dominique Coupe, Bruno Dambrine
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Patent number: 10569489Abstract: Compacting assembly comprising a shaper mold (24) defining an upwardly open housing suitable for receiving a woven preform (10a) that has previously been cut out, and a vertically movable compacting tool (128) that, together with the shaper mold (24), forms a compacting assembly for compacting said preform previously placed in the housing. The compacting tool (128) comprises at least a root portion (128A). The invention is applicable to fabricating turbine engine composite blades.Type: GrantFiled: October 3, 2014Date of Patent: February 25, 2020Assignee: Safran Aircraft EnginesInventors: Yann Marchal, Matthieu Gimat
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Patent number: 10508559Abstract: A fiber preform for a turbine engine blade or vane obtained by single-piece three-dimensional weaving. The preform includes a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.Type: GrantFiled: November 12, 2013Date of Patent: December 17, 2019Assignees: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Matthieu Gimat, Dominique Marie Christian Coupe
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Patent number: 10414487Abstract: An aircraft propeller blade including a streamlined structure constituted by at least one piece of fiber reinforcement obtained by three-dimensionally weaving yarns and densified by a matrix, together with a spar including an enlarged portion extending outside the fiber reinforcement and forming the root of the blade, and a shaping portion present in a housing arranged inside the fiber reinforcement. The fiber reinforcement includes a non-interlinked zone forming the housing inside the fiber reinforcement. The non-interlinked zone opens out into the bottom portion and into the rear edge of the fiber reinforcement so as to form an opening for inserting the shaping portion of the spar into the housing of the fiber reinforcement. The opening present in the rear edge of the fiber reinforcement extends over a height that is less than the height of the housing.Type: GrantFiled: June 25, 2014Date of Patent: September 17, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Adrien Laurenceau, Adrien Jacques Philippe Fabre, Matthieu Gimat
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Publication number: 20190024274Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.Type: ApplicationFiled: September 21, 2018Publication date: January 24, 2019Applicant: SNECMAInventors: Yann Marchal, Matthieu Gimat, Dominique Coupe, Bruno Dambrine
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Patent number: 10145039Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.Type: GrantFiled: April 17, 2013Date of Patent: December 4, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Yann Marchal, Matthieu Gimat, Dominique Coupe, Bruno Dambrine
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Patent number: 10131073Abstract: A fiber preform for a vane module of an intermediate casing of a turbine engine, the preform being obtained by three-dimensional weaving. The preform includes first longitudinal segment presenting opposite first and second ends and suitable for forming a first vane; a second longitudinal segment presenting first and second opposite ends and suitable for forming a second vane; and a first transverse segment connecting together the first and second longitudinal segments by their first ends, and suitable for forming a first transverse vane portion such as a flange or a platform.Type: GrantFiled: November 12, 2013Date of Patent: November 20, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Gimat, Dominique Coupe, Yann Marchal, Thierry Papin
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Patent number: 10041196Abstract: A fiber structure includes a blank portion formed as a single part by three-dimensional weaving between a first plurality of yarn layers and a second plurality of yarn layers, the blank portion corresponding to all or part of a fiber reinforcement preform for a part made of composite material. Outside the blank portion, the fiber structure includes one or more two-dimensional fabric layers, each two-dimensional fabric layer grouping together the yarns of a single layer belonging to at least the first plurality of yarn layers and situated outside the blank portion.Type: GrantFiled: September 29, 2014Date of Patent: August 7, 2018Assignees: SNECMA, SAFRANInventors: Matthieu Gimat, Yann Marchal, Dominique Coupe
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Patent number: 10019549Abstract: A method of designing a common preform for providing a plurality of preforms for turbine engine outlet guide vanes of different geometrical profiles and made out of composite material, the method including 3D geometrical modeling of the geometrical profiles of the different outlet guide vane preforms, flattening out each of the geometrical profiles of the different outlet guide vane preforms, superposing the geometrical profiles of the different flattened outlet guide vane preforms, and converging towards a single geometrical profile for an outlet guide vane preform common to all of the outlet guide vane preforms while guaranteeing identical positioning for the top and bottom regions of non-interlinking for all of the outlet guide vane preforms.Type: GrantFiled: September 24, 2015Date of Patent: July 10, 2018Assignees: SNECMA, SAFRANInventors: Matthieu Gimat, Dominique Marie Christian Coupe, Jean-Nöel Mahieu, Yann Didier Simon Marchal
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Patent number: 9919457Abstract: A method for forming a preform for a hollow turbomachine component is provided. The method includes positioning a sheet made of woven fibers on a base equipped with a longitudinal impression; positioning a mandrel in the longitudinal impression to clamp the sheet between the base and the mandrel, the mandrel having a thickness that increases between a proximal end and a distal end; locking the distal end of the mandrel into position; placing a proximal block resting on the base; forming two flaps of the sheet around the flanks of the mandrel; resting two lateral blocks on the base on either side of the mandrel; locking the lateral blocks into position to form an assembly; drying the assembly to form a preform including a flat base, from which two flaps extend perpendicularly; and adjusting the flaps to the dimensions of the mandrel by trimming excess material.Type: GrantFiled: August 14, 2013Date of Patent: March 20, 2018Assignee: SNECMAInventors: Richard Mathon, Dominique Magnaudeix, Noemie Souhaite, Yann Marchal, Matthieu Gimat
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Publication number: 20170276005Abstract: A composite material guide vane for a gas turbine engine, the composite material including fiber reinforcement densified by a matrix, the fiber reinforcement being formed as a single piece by three-dimensional weaving and including an airfoil and at least two fastener flanges extending from a radial end of the vane towards opposite side faces of the airfoil, the fastener flanges being axially offset from each other.Type: ApplicationFiled: August 18, 2015Publication date: September 28, 2017Inventors: Matthieu GIMAT, François CHARLEUX, Sébastien MARIN, Gwenael MARION
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Publication number: 20160288380Abstract: The invention relates to a compaction assembly comprising a shaping mold (24) delimiting an upwardly open housing, capable of receiving a woven preform cut out beforehand (10a), and a vertically moveable compaction tool (128) and forming, with the shaping mold, (24), a compaction assembly for said preform placed beforehand in the housing. The compaction tool (128) includes at least one foot portion (128A). The compaction tool (128) comprises at least three separate compaction blocks (1281-1287). Application to the manufacturing of composite fan blades for a turbomachine.Type: ApplicationFiled: October 3, 2014Publication date: October 6, 2016Applicant: SNECMAInventors: Yann MARCHAL, Jeremy ENGEL, Matthieu GIMAT
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Publication number: 20160245103Abstract: A fiber preform for a turbine engine blade or vane obtained by single-piece three-dimensional weaving. The preform includes a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.Type: ApplicationFiled: November 12, 2013Publication date: August 25, 2016Applicants: SNECMA, SAFRANInventors: Matthieu GIMAT, Dominique Marie, Christian COUPE
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Publication number: 20160243777Abstract: Compacting assembly comprising a shaper mold (24) defining an upwardly open housing suitable for receiving a woven preform (10a) that has previously been cut out, and a vertically movable compacting tool (128) that, together with the shaper mold (24), forms a compacting assembly for compacting said preform previously placed in the housing. The compacting tool (128) comprises at least a root portion (128A). The invention is applicable to fabricating turbine engine composite blades.Type: ApplicationFiled: October 3, 2014Publication date: August 25, 2016Applicant: SNECMAInventors: Yann MARCHAL, Matthieu GIMAT
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Publication number: 20160244897Abstract: A fiber structure includes a blank portion formed as a single part by three-dimensional weaving between a first plurality of yarn layers and a second plurality of yarn layers, the blank portion corresponding to all or part of a fiber reinforcement preform for a part made of composite material. Outside the blank portion, the fiber structure includes one or more two-dimensional fabric layers, each two-dimensional fabric layer grouping together the yarns of a single layer belonging to at least the first plurality of yarn layers and situated outside the blank portion.Type: ApplicationFiled: September 29, 2014Publication date: August 25, 2016Inventors: Matthieu GIMAT, Yann MARCHAL, Dominique COUPE
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Publication number: 20160159460Abstract: An aircraft propeller blade including a streamlined structure constituted by at least one piece of fiber reinforcement obtained by three-dimensionally weaving yarns and densified by a matrix, together with a spar including an enlarged portion extending outside the fiber reinforcement and forming the root of the blade, and a shaping portion present in a housing arranged inside the fiber reinforcement. The fiber reinforcement includes a non-interlinked zone forming the housing inside the fiber reinforcement. The non-interlinked zone opens out into the bottom portion and into the rear edge of the fiber reinforcement so as to form an opening for inserting the shaping portion of the spar into the housing of the fiber reinforcement. The opening present in the rear edge of the fiber reinforcement extends over a height that is less than the height of the housing.Type: ApplicationFiled: June 25, 2014Publication date: June 9, 2016Applicant: SNECMAInventors: Adrien Laurenceau, Adrien Jacques, Philippe Fabre, Matthieu Gimat
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Publication number: 20160012178Abstract: A method of designing a common preform for providing a plurality of preforms for turbine engine outlet guide vanes of different geometrical profiles and made out of composite material, the method including 3D geometrical modeling of the geometrical profiles of the different outlet guide vane preforms, flattening out each of the geometrical profiles of the different outlet guide vane preforms, superposing the geometrical profiles of the different flattened outlet guide vane preforms, and converging towards a single geometrical profile for an outlet guide vane preform common to all of the outlet guide vane preforms while guaranteeing identical positioning for the top and bottom regions of non-interlinking for all of the outlet guide vane preforms.Type: ApplicationFiled: September 24, 2015Publication date: January 14, 2016Inventors: Matthieu GIMAT, Dominique Marie Christian COUPE, Jean-Noël MAHIEU, Yann Didier Simon MARCHAL
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Publication number: 20150354377Abstract: A fiber preform for a vane module of an intermediate casing of a turbine engine, the preform being obtained by three-dimensional weaving. The preform includes first longitudinal segment presenting opposite first and second ends and suitable for forming a first vane; a second longitudinal segment presenting first and second opposite ends and suitable for forming a second vane; and a first transverse segment connecting together the first and second longitudinal segments by their first ends, and suitable for forming a first transverse vane portion such as a flange or a platform.Type: ApplicationFiled: November 12, 2013Publication date: December 10, 2015Inventors: Matthieu GIMAT, Dominique COUPE, Yann MARCHAL, Thierry PAPIN