Patents by Inventor Gilles Pierre-Marie NOTARIANNI
Gilles Pierre-Marie NOTARIANNI 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: 11795825Abstract: The invention relates to an inter-blade platform of a turbomachine fan, comprising: —a base comprising a first surface configured to delimit a flow path in the fan and a second surface on the opposite side from the first surface, —two flanks extending radially next to the second surface, each of the flanks having a sacrificial free end configured to bear against a fan disc.Type: GrantFiled: June 22, 2020Date of Patent: October 24, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Teddy Fixy, Jérémy Guivarc'h, Gilles Pierre-Marie Notarianni, Thomas Alain De Gaillard
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Patent number: 11773733Abstract: A fibrous texture forming the fibrous reinforcement of a turbomachine blade made of composite material which has a three-dimensional weaving between warp yarns or strands made of first fibers and weft yarns or strands made of first fibers, the texture including a blade root portion, a blade airfoil portion and a free end, the texture extending along the transverse direction between a first edge corresponding to a leading edge of the blade and a second edge corresponding to a trailing edge of the blade. The blade airfoil portion has a reinforced area extending along the longitudinal direction from the free end over a first length, and along the transverse direction from the second edge over a second length less, the reinforced area including weft yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than the first fibers.Type: GrantFiled: March 18, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie Notarianni, Teddy Fixy, Paula Salas De Los Rios
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Publication number: 20230119475Abstract: A fibrous texture forming the fibrous reinforcement of a turbomachine blade made of composite material which has a three-dimensional weaving between warp yarns or strands made of first fibers and weft yarns or strands made of first fibers, the texture including a blade root portion, a blade airfoil portion and a free end, the texture extending along the transverse direction between a first edge corresponding to a leading edge of the blade and a second edge corresponding to a trailing edge of the blade. The blade airfoil portion has a reinforced area extending along the longitudinal direction from the free end over a first length, and along the transverse direction from the second edge over a second length less, the reinforced area including weft yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than the first fibers.Type: ApplicationFiled: March 18, 2021Publication date: April 20, 2023Inventors: Gilles Pierre-Marie NOTARIANNI, Teddy FIXY, Paula SALAS DE LOS RIOS
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Publication number: 20220228490Abstract: The invention relates to an inter-blade platform of a turbomachine fan, comprising: —a base comprising a first surface configured to delimit a flow path in the fan and a second surface on the opposite side from the first surface, —two flanks extending radially next to the second surface, each of the flanks having a sacrificial free end configured to bear against a fan disc.Type: ApplicationFiled: June 22, 2020Publication date: July 21, 2022Applicant: Safran Aircraft EnginesInventors: Teddy FIXY, Jérémy GUIVARC'H, Gilles Pierre-Marie NOTARIANNI, Thomas Alain DE GAILLARD
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Patent number: 11377973Abstract: A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.Type: GrantFiled: May 16, 2019Date of Patent: July 5, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Eddy Keomorakott Souryavongsa, Thomas Alain De Gaillard, Teddy Fixy, Gilles Pierre-Marie Notarianni
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Patent number: 11371357Abstract: The invention concerns a fan blade for a turbomachine, comprising: a leading edge and a pressure-side wall, a structural shield, said shield being attached and fixed to the leading edge of the blade and comprising a pressure-side fin attached to the pressure-side wall, and a piece of fabric comprising aramid fibres, attached and fixed to the pressure-side wall of the fan blade such that the piece of fabric extends in the continuation of the pressure-side fin of the shield without covering said pressure-side fin.Type: GrantFiled: May 23, 2019Date of Patent: June 28, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Alain De Gaillard, Audrey Myriam Laguerre, Gilles Pierre-Marie Notarianni
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Publication number: 20210372428Abstract: The invention relates to a blade (3) of a fan (1) of a turbomachine having a structure made of a composite material comprising a fibrous reinforcement (5) obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement (5) is embedded, the fibrous reinforcement (5) comprising first strands (9) having a predetermined elongation at break, a portion of the fibrous reinforcement (5) further comprising second strands (10) having an elongation at break higher than that of the first strands (9).Type: ApplicationFiled: October 30, 2019Publication date: December 2, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Alain DE GAILLARD, Gilles Pierre-Marie NOTARIANNI, Frédéric Jean-Bernard POUZADOUX
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Patent number: 11105210Abstract: 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: GrantFiled: September 27, 2016Date of Patent: August 31, 2021Assignee: 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: 20210215049Abstract: The invention concerns a fan blade (1) for a turbomachine, comprising: —a leading edge (4) and a pressure-side wall (6), —a structural shield (10), said shield (10) being attached and fixed to the leading edge (4) of the blade (1) and comprising a pressure-side fin (11) attached to the pressure-side wall (6), and —a piece of fabric (20) comprising aramid fibres, attached and fixed to the pressure-side wall (6) of the fan blade (1) such that the piece of fabric (20) extends in the continuation of the pressure-side fin (11) of the shield (10) without covering said pressure-side fin (11).Type: ApplicationFiled: May 23, 2019Publication date: July 15, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Alain DE GAILLARD, Audrey Myriam LAGUERRE, Gilles Pierre-Marie NOTARIANNI
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Publication number: 20210199018Abstract: A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.Type: ApplicationFiled: May 16, 2019Publication date: July 1, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Eddy Keomorakott Souryavongsa, Thomas Alain De Gaillard, Teddy Fixy, Gilles Pierre-Marie Notarianni
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Patent number: 11040465Abstract: 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: GrantFiled: February 19, 2018Date of Patent: June 22, 2021Assignee: Safran Aircraft EnginesInventors: Jérémy Guivarc'h, Alexandre Bernard Marie Boisson, Thomas Alain De Gaillard, Gilles Pierre-Marie Notarianni
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Patent number: 10883374Abstract: 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: GrantFiled: September 27, 2016Date of Patent: January 5, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie Notarianni, Jeremy Guivarc'H, Frederic Jean-Bernard Pouzadoux, Dominique Raulin, Thibault Ruf
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Patent number: 10844725Abstract: A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.Type: GrantFiled: December 21, 2016Date of Patent: November 24, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Jean-Bernard Pouzadoux, Alain Jacques Michel Bassot, Jérémy Guivarc'h, Gilles Pierre-Marie Notarianni, Thibault Ruf
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Publication number: 20200270997Abstract: A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.Type: ApplicationFiled: December 21, 2016Publication date: August 27, 2020Inventors: Frédéric Jean-Bernard POUZADOUX, ALAIN JACQUES MICHEL BASSOT, Jérémy GUIVARC'H, GILLES PIERRE-MARIE NOTARIANNI, THIBAULT RUF
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Patent number: 10689996Abstract: A turbomachine blade (10) comprising a body (11) and an elastomer gasket (12) fastened to said body (11).Type: GrantFiled: June 16, 2017Date of Patent: June 23, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie Notarianni, Audrey Laguerre, Stephane Roger Mahias
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Patent number: 10570757Abstract: A turbomachine rotary assembly includes a plurality of blades having roots positioned in the grooves of a rotor disk and an axial retention system of the blades. The axial retention system includes a removable lock mounted bearing against the upstream axial ends of two consecutive teeth of the disk so as to block the opening of the groove formed by the teeth. It includes removable parts suitable for being mounted at the upstream axial ends of the teeth and to block the lock by clamping the lock between the removable parts and the teeth once the lock is installed against the upstream axial ends of the teeth.Type: GrantFiled: October 19, 2017Date of Patent: February 25, 2020Assignee: Safran Aircraft EnginesInventors: Thomas Alain De Gaillard, Alexandre Bernard Marie Boisson, Gilles Pierre-Marie Notarianni, Charles-Henri Claude Jacky Sullet
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Patent number: 10533574Abstract: The invention relates to a blade made of composite material, provided with a reinforcement (17) made of a stronger material with regard to a leading edge (5) likely to be struck by solid objects, which comprises, under the aerodynamic portion of the blade, extensions (18, 19) attached to the blade root. According to the invention, the extensions (18, 19) are dissymmetric, the extension (18) located on the suction side being generally further back from the leading edge (5) than the extension (19) on the pressure side.Type: GrantFiled: April 28, 2016Date of Patent: January 14, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Damiens, Frédéric Jean-Bernard Pouzadoux, Gilles Pierre-Marie Notarianni
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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: 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: 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