Patents by Inventor Jérémy GUIVARC'H
Jérémy GUIVARC'H 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: 10619486Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).Type: GrantFiled: December 21, 2016Date of Patent: April 14, 2020Assignee: Safran Aircraft EnginesInventors: Frédéric Jean-Bernard Pouzadoux, Alain Jacques Michel Bassot, Jérémy Guivarc'h, Jean-Louis Romero, Thibault Ruf
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Publication number: 20200108565Abstract: A method for producing a part. This part including a surface portion whereon is positioned an element to be assembled via an adhesive on the surface portion. The method includes the steps of: mounting a sleeve of heat-shrinkable material around at least one portion of the element on the part, heating of the sleeve in order to shrink it and thus to apply an application force of the element on the surface portion, hardening of the adhesive, and removing the sleeve.Type: ApplicationFiled: October 1, 2019Publication date: April 9, 2020Inventors: Jeremy GUIVARC'H, Pierre Antoine BOSSAN, Michael Patrick GRAMZOW, Sebastien MARIN
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Publication number: 20190390559Abstract: A fan includes: a fan disc; an inter-blade platform including a base and a radial tab, a second orifice being formed in the tab of the platform; and a lock having a downstream edge configured to bear against the tab of the platform. The one among the downstream edge and the yoke of the fan disc includes a pin, the other includes a first orifice, the pin being configured to enter the first orifice and the second orifice so as to block the platform relative to the fan disc.Type: ApplicationFiled: June 20, 2019Publication date: December 26, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jeremy GUIVARC'H, Fabrice Michel Francois Rene AUBERT, Pierre Martin MICHELSEN
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Publication number: 20190381696Abstract: A fiber preform for a turbine engine blade, the preform comprising a main fiber structure (40) obtained by a single piece of three-dimensional weaving, said main first structure (40) comprising a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) and suitable for forming an airfoil portion (22), and a first transverse segment (51) extending transversely from the junction (49) between the first and second longitudinal segments (41, 42) and suitable for forming a first tongue for a first platform, wherein the first transverse segment (51) extends axially over a length that is less than 30%, preferably less than 15%, of the length of the junction (49) between the first and second longitudinal segments (41, 42).Type: ApplicationFiled: February 19, 2018Publication date: December 19, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy GUIVARC'H, Alexandre Bernard Marie BOISSON, Thomas Alain DE GAILLARD, Gilles Pierre-Marie NOTARIANNI
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Patent number: 10436036Abstract: A fitted platform for positioning between two adjacent blades of an aviation turbine engine fan includes a flow passage wall made of composite material having a central portion, and first and second margins each extending in a longitudinal direction of the wall. Each margin extends over a determined distance from the central portion in a transverse direction of the wall. The flow passage wall includes a fiber reinforcement densified by a matrix. The fiber reinforcement present in the central portion presents three-dimensional weaving, and the fiber reinforcement present in the first and second margins presents two-dimensional weaving, at least in part.Type: GrantFiled: July 5, 2016Date of Patent: October 8, 2019Assignee: Safran Aircraft EnginesInventors: Jeremy Guivarc'h, Francois Charleux
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Patent number: 10240463Abstract: A blade made of organic matrix composite material for a gas turbine aeroengine, includes an airfoil extending transversely between a leading edge and a trailing edge; and a metal strip positioned on the leading edge of the airfoil, the metal strip having two flanges extending on either side of the leading edge over portions of the side faces of the airfoil forming a pressure side face and a suction side face so that the strip fits closely to the profile of the leading edge, the metal strip being fastened to the leading edge of the airfoil by at least one stitching thread; wherein the stitching thread has at least one external thread segment extending substantially transversely between a hole formed through a flange of the strip and a passage formed in a portion of the airfoil that has at least one face that is not covered by the metal strip.Type: GrantFiled: March 15, 2016Date of Patent: March 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie Notarianni, Matthieu Arnaud Gimat, Jérémy Guivarc'h, Thibault Ruf
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Publication number: 20190024512Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).Type: ApplicationFiled: December 21, 2016Publication date: January 24, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy GUIVARC'H, Alain Jacques Michel BASSOT, Gérald DIOGO, Jean-Louis ROMERO, Thibault RUF
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Publication number: 20190010807Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).Type: ApplicationFiled: December 21, 2016Publication date: January 10, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Jean-Bernard POUZADOUX, Alain Jacques Michel BASSOT, Jérémy GUIVARC'H, Jean-Louis ROMERO, Thibault RUF
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Publication number: 20190003312Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) including a pressure-side wing (34) and a suction-side wing (36). Each pressure-side wing (34) and suction-side wing (36) extends heightwise from a bottom edge (50) to a top edge (51) and lengthwise from the leading edge (18) to a rear edge (40, 42), and they are connected together via the leading edge (18), and wherein the rear edge (42) of the suction-side wing (36) presents at least one shaped segment (S1, S2) that is shaped in such a manner that the length of the suction-side wing (36) within this segment is shorter than the length (l2, l3, l21, l22, l31, l32) of the suction-side wing (36) at each end of this segment (S1, S2).Type: ApplicationFiled: December 21, 2016Publication date: January 3, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Jean-Bernard POUZADOUX, Alain Jacques Michel BASSOT, Jérémy GUIVARC'H, Jean-Louis ROMERO, Thibault RUF
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Publication number: 20180274374Abstract: The invention provides a blade (16) comprising a blade body (30) made of organic matrix composite material reinforced by fibers and a leading edge shield (32) made of a material that withstands point impacts better than the composite material of the blade body. The leading edge shield (32) is assembled on the blade body (30) and the blade (16) includes bonding reinforcement (46) adhesively bonded on the leading edge shield (32) and on the blade body (16). The invention also provides a turbojet including a fan including such blades, and also a method of fabricating such a blade.Type: ApplicationFiled: September 27, 2016Publication date: September 27, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Arnaud GIMAT, Jérémy GUIVARC'H, Gilles Pierre-Marie NOTARIANNI, Frédéric Jean-Bernard POUZADOUX, Thibault RUF
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Publication number: 20180274375Abstract: A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.Type: ApplicationFiled: September 27, 2016Publication date: September 27, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie NOTARIANNI, Jeremy GUIVARC'H, Frederic Jean-Bernard POUZADOUX, Dominique RAULIN, Thibault RUF
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Publication number: 20180230825Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).Type: ApplicationFiled: August 2, 2016Publication date: August 16, 2018Applicant: Safran Aircraft EnginesInventors: Matthieu Arnaud Gimat, Alain Jacques Michel BASSOT, Jérémy GUIVARC'H, Jean-Noël MAHIEU, Thibault RUF
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Publication number: 20180010462Abstract: The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said wall, each margin extending over a determined distance (D) from the central portion (16) in a transverse direction of said wall, said flow passage wall comprising fiber reinforcement densified by a matrix, the platform being characterized in that the fiber reinforcement present in the central portion (16) presents three-dimensional weaving, and in that the fiber reinforcement present in the first and second margins (18) presents two-dimensional weaving, at least in part. The invention also provides a fan module, a turbine engine, and a method of fabricating such a platform.Type: ApplicationFiled: July 5, 2016Publication date: January 11, 2018Applicant: Safran Aircraft EnginesInventors: Jeremy GUIVARC'H, Francois Charleux
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Publication number: 20160312616Abstract: A blade made of organic matrix composite material for a gas turbine aeroengine, includes an airfoil extending transversely between a leading edge and a trailing edge; and a metal strip positioned on the leading edge of the airfoil, the metal strip having two flanges extending on either side of the leading edge over portions of the side faces of the airfoil forming a pressure side face and a suction side face so that the strip fits closely to the profile of the leading edge, the metal strip being fastened to the leading edge of the airfoil by at least one stitching thread; wherein the stitching thread has at least one external thread segment extending substantially transversely between a hole formed through a flange of the strip and a passage formed in a portion of the airfoil that has at least one face that is not covered by the metal strip.Type: ApplicationFiled: March 15, 2016Publication date: October 27, 2016Inventors: Gilles Pierre-Marie NOTARIANNI, Matthieu Arnaud GIMAT, Jérémy GUIVARC'H, Thibault RUF