Patents by Inventor Thomas Alain DE GAILLARD

Thomas Alain DE GAILLARD 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: 11371357
    Abstract: 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: Grant
    Filed: May 23, 2019
    Date of Patent: June 28, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Audrey Myriam Laguerre, Gilles Pierre-Marie Notarianni
  • Patent number: 11313239
    Abstract: A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of radial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.
    Type: Grant
    Filed: May 20, 2019
    Date of Patent: April 26, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Alexandre Bernard Marie Boisson, Rémi Roland Robert Mercier, Alexis Thomas Chaboud
  • Publication number: 20220025900
    Abstract: The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).
    Type: Application
    Filed: December 13, 2019
    Publication date: January 27, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas, Alain DE GAILLARD, Benjamin BULOT, Eddy, Keomorakott SOURYAVONGSA
  • Publication number: 20210396142
    Abstract: The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement Obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded. According to the invention, the fibrous reinforcement comprises a first portion forming the leading edge and a second portion forming all or part of the trailing edge, and the strands of the fibrous reinforcement comprise first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.
    Type: Application
    Filed: October 30, 2019
    Publication date: December 23, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain DE GAILLARD, Jérémy GUIVARC'H, Paula SALAS DE LOS RIOS
  • Publication number: 20210372428
    Abstract: 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: Application
    Filed: October 30, 2019
    Publication date: December 2, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain DE GAILLARD, Gilles Pierre-Marie NOTARIANNI, Frédéric Jean-Bernard POUZADOUX
  • Patent number: 11168567
    Abstract: A fibrous texture to form the fibrous reinforcement of a turbomachine blade made of composite material, the texture being made in one piece and having a three-dimensional weaving, and includes blade root, blade airfoil and blade support portions. The blade support portion includes a first area extending transversely from a first edge of the texture to form a leading edge and a second area extending transversely from the first area up to a second edge of the texture to form a trailing edge, the first area including warp yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than that of the first fibers, the first area having a first volume ratio in yarns or strands made of second fibers strictly greater than a second volume ratio in yarns or strands made of second fibers in the second area.
    Type: Grant
    Filed: October 8, 2019
    Date of Patent: November 9, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Pascal Jean-Charles Gondre, Thomas Alain De Gaillard
  • Patent number: 11105208
    Abstract: A platform for a fan of a turbomachine that will be mounted on a hub of the fan between two adjacent blades, the platform comprising a principal wall with a longitudinal principal orientation, that has a curved shape along the longitudinal direction, and a stiffener that is mounted on a lower face of the principal wall, of which the section of the stiffener, in a plane perpendicular to the longitudinal direction is globally in the form of a U open towards the principal wall. The stiffener comprises at least two straight segments inclined relative to each other and inclined relative to the longitudinal principal direction.
    Type: Grant
    Filed: July 19, 2019
    Date of Patent: August 31, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Claire Marie Figeureu, Thomas Alain De Gaillard, Oscar-Emmanuel Gnangnon
  • Publication number: 20210215049
    Abstract: 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: Application
    Filed: May 23, 2019
    Publication date: July 15, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain DE GAILLARD, Audrey Myriam LAGUERRE, Gilles Pierre-Marie NOTARIANNI
  • Publication number: 20210199018
    Abstract: 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: Application
    Filed: May 16, 2019
    Publication date: July 1, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Eddy Keomorakott Souryavongsa, Thomas Alain De Gaillard, Teddy Fixy, Gilles Pierre-Marie Notarianni
  • Publication number: 20210189893
    Abstract: A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of axial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.
    Type: Application
    Filed: May 20, 2019
    Publication date: June 24, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain DE GAILLARD, Alexandre Bernard Marie BOISSON, Rémi Roland Robert MERCIER, Alexis Thomas CHABOUD
  • Patent number: 11040465
    Abstract: 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: Grant
    Filed: February 19, 2018
    Date of Patent: June 22, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Jérémy Guivarc'h, Alexandre Bernard Marie Boisson, Thomas Alain De Gaillard, Gilles Pierre-Marie Notarianni
  • Patent number: 11021973
    Abstract: A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.
    Type: Grant
    Filed: March 20, 2017
    Date of Patent: June 1, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Alexandre Bernard Marie Boisson
  • Patent number: 11015462
    Abstract: A blade body made of composite material includes fiber reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a root or bottom portion and a tip or top portion, and in a transverse direction between a leading edge and a trailing edge. The fiber reinforcement of the blade body includes a first portion constituted by a plurality of yarn layers interlinked by three-dimensional or multilayer weaving, and a second portion forming all or part of at least one leading edge or at least one trailing edge of a blade. The second portion includes a plurality of short fibers oriented in random manner, the yarns of the plurality of yarn layers of the first portion and the short fibers of the second portion being embedded in the matrix.
    Type: Grant
    Filed: May 21, 2019
    Date of Patent: May 25, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Clément Pierre Postec, Charles-Henri Claude Jacky Sullet
  • Patent number: 10710704
    Abstract: A fairing ring for a bladed wheel is disclosed. The fairing ring includes an annular wall extending axially, the wall presenting a plurality of notches extending axially, each notch being configured to receive a leading edge or a trailing edge of a blade.
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: July 14, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Alexandre Bernard Marie Boisson, Claire Marie Figeureu
  • Patent number: 10670038
    Abstract: Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P?) perpendicular to the axis of elongation and intersecting the platform, the dist
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: June 2, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, William Henri Joseph Riera, Guillaume Olivier Vartan Martin
  • Patent number: 10619493
    Abstract: A preform for a turbine engine blade, the preform being obtained by three-dimensional weaving and comprising a first longitudinal segment (31) suitable for forming at least a portion of a blade root, a second longitudinal segment (32) extending the first longitudinal segment (31) upwards, and suitable for forming at least a portion of a stilt portion, a third longitudinal segment (33) extending the second longitudinal segment (32) upwards, and suitable for forming an airfoil portion, a first transverse segment (34) extending transversely from the junction between the second and third longitudinal segments (32, 33), and suitable for forming a first platform, and a first oblique segment (36) extending from the junction between the first and second longitudinal segments (31, 32) to the first transverse segment (34), and suitable for forming a retaining leg (26) for the first platform.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: April 14, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Caroline Jacqueline Denise Berdou, Alexandre Bernard Marie Boisson, Matthieu Arnaud Gimat
  • Publication number: 20200109634
    Abstract: A fibrous texture to form the fibrous reinforcement of a turbomachine blade made of composite material, the texture being made in one piece and having a three-dimensional weaving, and includes blade root, blade airfoil and blade support portions. The blade support portion includes a first area extending transversely from a first edge of the texture to form a leading edge and a second area extending transversely from the first area up to a second edge of the texture to form a trailing edge, the first area including warp yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than that of the first fibers, the first area having a first volume ratio in yarns or strands made of second fibers strictly greater than a second volume ratio in yarns or strands made of second fibers in the second area.
    Type: Application
    Filed: October 8, 2019
    Publication date: April 9, 2020
    Inventors: Guillaume Pascal Jean-Charles GONDRE, Thomas Alain DE GAILLARD
  • Patent number: 10612558
    Abstract: A rotary assembly of an aviation turbine engine, includes a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk. The tooth of the fan disk includes a tab extending the tooth axially upstream, and the platform includes a locking ring at its upstream end for receiving the tab of the tooth of the fan disk. The assembly further includes a spacer positioned inside the locking ring so as to block the platform on the tab of the tooth of the fan disk.
    Type: Grant
    Filed: July 6, 2016
    Date of Patent: April 7, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Alexandre Bernard Marie Boisson, Matthieu Arnaud Gimat, Audrey Laguerre
  • Patent number: 10570757
    Abstract: 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: Grant
    Filed: October 19, 2017
    Date of Patent: February 25, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Thomas Alain De Gaillard, Alexandre Bernard Marie Boisson, Gilles Pierre-Marie Notarianni, Charles-Henri Claude Jacky Sullet
  • Patent number: 10556367
    Abstract: A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: February 11, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sébastien Marin, Thomas Alain De Gaillard, Audrey Laguerre