Patents by Inventor Sébastien PAUTARD
Sébastien PAUTARD 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).
-
Patent number: 10899051Abstract: A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method including in succession placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade, closing the injection mold, injecting a thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip, compacting the assembly, solidifying the resin by regulating the temperature of the injection mold, and unmolding the resulting blade.Type: GrantFiled: July 22, 2014Date of Patent: January 26, 2021Assignee: SAFRANInventor: Sebastien Pautard
-
Patent number: 10532521Abstract: A method of fabricating a composite material part having a body secured to at least one platform present at one end of the body, the method including using the fiber blank to form a preform for the part that is to be made by folding out segments of the second and third portions that are not interlinked with the first portion on opposite sides of the first portion, by shaping the folded-out segments of the second and third portions to form preform portions for a platform of the part to be fabricated, and by folding down the segment of the first portion in order to fill in the groove present in the gap between the second and third portions; and densifying the preform with a matrix in order to obtain a part made of composite material having at least one integrated platform.Type: GrantFiled: November 3, 2016Date of Patent: January 14, 2020Assignee: SAFRANInventors: Nicolas Pierre Lanfant, Sébastien Pautard
-
Publication number: 20180319101Abstract: A method of fabricating a composite material part having a body secured to at least one platform present at one end of the body, the method including using the fiber blank to form a preform for the part that is to be made by folding out segments of the second and third portions that are not interlinked with the first portion on opposite sides of the first portion, by shaping the folded-out segments of the second and third portions to form preform portions for a platform of the part to be fabricated, and by folding down the segment of the first portion in order to fill in the groove present in the gap between the second and third portions; and densifying the preform with a matrix in order to obtain a part made of composite material having at least one integrated platform.Type: ApplicationFiled: November 3, 2016Publication date: November 8, 2018Inventors: Nicolas Pierre LANFANT, Sébastien PAUTARD
-
Patent number: 9784112Abstract: The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.Type: GrantFiled: October 10, 2014Date of Patent: October 10, 2017Assignees: SNECMA, SAFRANInventors: Maxime Briend, Sebastien Pautard
-
Publication number: 20170254212Abstract: A guide vane for a gas turbine engine, the guide vane including an airfoil made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers agglomerated in the form of a mat, the airfoil being provided at least on a leading edge with a reinforcing strip, the reinforcing strip being made from a single strip of unidirectional fabric or of textile, or by stacking a plurality of pre-impregnated plies of unidirectional fabric or of textile made of carbon fibers or of glass fibers, and at least one platform positioned at a radial end of the airfoil, the platform being made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers.Type: ApplicationFiled: August 20, 2015Publication date: September 7, 2017Applicants: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Sébastien PAUTARD, Maxime BRIEND, Emilie TROUSSET, Patrick DUNLEAVY
-
Patent number: 9725182Abstract: An aeroengine control device including a mount and having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel. Each lever is movable between a rest position and a maximum actuation position. The secondary lever is mounted to pivot on the main lever. Cam paths are mounted on the code wheel and on the mount in such a manner that the main lever can move the code wheel when the main lever is moved while the secondary lever is in the rest position. The secondary lever can move the code wheel when the secondary lever is moved while the main lever is in the rest position, with movement of either lever being prevented when the other lever is clearly away from its rest position.Type: GrantFiled: September 30, 2013Date of Patent: August 8, 2017Assignee: Safran Electronics & DefenseInventors: Hafid Elabellaoui, Jean-Eric Besold, Sebastien Pautard, Thierry Cartry, David Engler, Etienne Merlet
-
Patent number: 9470502Abstract: Flow valve including a casing containing an electromagnetic assembly for detecting a magnetic field. The electromagnetic assembly is fixed to a pendulum suspended by an articulation from a plate of the casing. The casing contains a liquid for damping the movements of the pendulum. The pendulum includes a surface opposite the articulation which has a spherical cap shape and which extends facing a wall of the casing of complementary shape, defining a space having dimensions suitable for producing a laminar rolling of the damping liquid between them when the pendulum is in motion.Type: GrantFiled: April 19, 2012Date of Patent: October 18, 2016Assignee: SAGEM DEFENSE SECURITEInventors: Christian Cardoso, Didier Habert, Etienne Merlet, Fabrice Jean, Mickael Magalhaes, Sebastien Pautard
-
Publication number: 20160176124Abstract: A method of injection molding a part made of composite material including fiber reinforcement densified by a matrix, the method including, in succession, placing a fiber preform in an injection mold, injecting a thermoplastic resin under pressure so as to impregnate the preform, and polymerizing the resin, the fiber preform being consolidated in the injection mold prior to injecting the resin.Type: ApplicationFiled: July 21, 2014Publication date: June 23, 2016Applicant: SAFRANInventors: Bastien TRANQUART, Sebastien PAUTARD
-
Publication number: 20160167269Abstract: A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method including in succession placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade, closing the injection mold, injecting a thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip, compacting the assembly, solidifying the resin by regulating the temperature of the injection mold, and unmolding the resulting blade.Type: ApplicationFiled: July 22, 2014Publication date: June 16, 2016Applicant: SAFRANInventor: Sebastien PAUTARD
-
Publication number: 20160153295Abstract: A composite vane for a turbine engine, the vane having a pressure side face (12) and a suction side face (14) that define the aerodynamic profile of the vane, the vane (10) comprising: a metallic core (20) forming the pressure side face (12) or the suction side face (14) of the vane; and an organic matrix (30) associated with the metallic core (20).Type: ApplicationFiled: October 29, 2014Publication date: June 2, 2016Applicants: SAFRAN, SNECMAInventors: Sebastien PAUTARD, Maxime BRIEND
-
Patent number: 9284842Abstract: A link part for a turbine engine which mounted between a fan cone and a fan disk supporting fan blades is provided. The link part includes an annular wall pierced by a plurality of orifices, each orifice for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform. The annular wall is made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform.Type: GrantFiled: February 7, 2013Date of Patent: March 15, 2016Assignees: SAFRAN, SNECMAInventors: Jean-Pierre Francois Lombard, Wouter Balk, Sebastien Pautard, Benjamin Samson, Benjamin Kiener-Calvet, Frederic Rogues
-
Publication number: 20150104299Abstract: The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.Type: ApplicationFiled: October 10, 2014Publication date: April 16, 2015Applicants: SNECMA, SAFRANInventors: Maxime BRIEND, Sebastien PAUTARD
-
Publication number: 20140190304Abstract: An aeroengine control device comprising a mount, having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel, each lever being movable between a rest position and a maximum actuation position, the secondary lever being mounted to pivot on the main lever. A connecting rod connects the secondary lever in permanent manner to the code wheel and the main lever is provided with a connection member arranged to co-operate with a portion in relief secured to the code wheel and with a portion in relief secured to the mount in such a manner that the connection member attaches to the code wheel when the main lever is moved while the secondary lever is in its rest position and attaches to the mount, thereby releasing the code wheel to turn, when the secondary lever is moved while the main lever is in its rest position, while movement of either lever is prevented when the other lever is away from its rest position.Type: ApplicationFiled: October 5, 2010Publication date: July 10, 2014Inventors: Aurelie Besold, David ENGLER, Sebastien PAUTARD, Antoine Besold, Stephanie Besold, Hafid ELABELLAOUI, Marie-Noel Besold, Etienne MERLET
-
Publication number: 20140061389Abstract: An aeroengine control device including a mount and having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel. Each lever is movable between a rest position and a maximum actuation position. The secondary lever is mounted to pivot on the main lever. Cam paths are mounted on the code wheel and on the mount in such a manner that the main lever can move the code wheel when the main lever is moved while the secondary lever is in the rest position. The secondary lever can move the code wheel when the secondary lever is moved while the main lever is in the rest position, with movement of either lever being prevented when the other lever is clearly away from its rest position.Type: ApplicationFiled: September 30, 2013Publication date: March 6, 2014Applicant: SAGEM DEFENSE SECURITEInventors: Hafid ELABELLAOUI, Jean-Eric BESOLD, Sebastien PAUTARD, Thierry CARTRY, David ENGLER, Etienne MERLET
-
Publication number: 20140015519Abstract: Flow valve comprising a casing (1) containing an electromagnetic assembly (2) for detecting a magnetic field, the electromagnetic assembly being fixed to a pendulum (3) suspended by an articulation (6) from a wall (5) of the casing, the casing containing a liquid for damping the movements of the pendulum, characterized in that the pendulum comprises opposite the articulation a surface (8) which has a spherical cap shape and which extends facing a wall (4) of the casing of complementary shape, defining a space having, dimensions suitable for producing a laminar rolling of the damping liquid between them, when the pendulum is in motion.Type: ApplicationFiled: April 19, 2011Publication date: January 16, 2014Applicant: SAGEM DEFENSE SECURITEInventors: Christian Cardoso, Didier Habert, Etienne Merlet, Fabrice Jean, Mickael Magalhaes, Sebastien Pautard