Patents by Inventor Josselin Luc Florent SICARD

Josselin Luc Florent SICARD 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).

  • Device for sealing between a rotor and a stator of a turbine engine
    Patent number: 11441442
    Abstract: A sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: September 13, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Baptiste Marie Aubin Pierre Jouy, Josselin Luc Florent Sicard, Mathieu Charles Jean Verdiere, Loïc Fabien François Villard
  • Turbo engine rotor disc
    Patent number: 10954795
    Abstract: A turbo engine rotor disc that has a rotation axis and includes, at the periphery thereof, a plurality of slots regularly distributed around the rotation axis, wherein at least one slot of the plurality of slots has a base that has a plurality of plates arranged in staggered rows and protruding from the base, each plate extending mainly along a direction perpendicular to a radial direction.
    Type: Grant
    Filed: July 21, 2017
    Date of Patent: March 23, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benoît Guillaume Silet, Youki Olivier Ito-Lardeau, Gilles Marcel Jeannin, Baptiste Marie Aubin Pierre Jouy, Bertrand Guillaume Robin Pellaton, Josselin Luc Florent Sicard
  • DEVICE FOR SEALING BETWEEN A ROTOR AND A STATOR OF A TURBINE ENGINE
    Publication number: 20200095882
    Abstract: This concerns a sealing device between a rotor part and a stator part, comprising at least one abradable coating (46) cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device comprises a circumferential wall (54) that radially extends beyond the upstream free axial sealing surface (48a) of the coating (46) to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.
    Type: Application
    Filed: April 24, 2018
    Publication date: March 26, 2020
    Inventors: Baptiste Marie Aubin Pierre JOUY, Josselin Luc Florent SICARD, Mathieu Charles Jean VERDIERE, Loïc Fabien François VILLARD
  • Turbine rotor for a gas turbine engine
    Patent number: 10526893
    Abstract: A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: January 7, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Josselin Luc Florent Sicard, Bertrand Pellaton, Hélène Marie Barret, Benoit Guillaume Silet, Anne-Flore Karine Houlet
  • TURBO ENGINE ROTOR DISC
    Publication number: 20190169991
    Abstract: A turbo engine rotor disc that has a rotation axis and includes, at the periphery thereof, a plurality of slots regularly distributed around the rotation axis, wherein at least one slot of the plurality of slots has a base that has a plurality of plates arranged in staggered rows and protruding from the base, each plate extending mainly along a direction perpendicular to a radial direction.
    Type: Application
    Filed: July 21, 2017
    Publication date: June 6, 2019
    Inventors: Benoît Guillaume SILET, Youki Olivier ITO-LARDEAU, Gilles Marcel JEANNIN, Baptiste Marie Aubin Pierre JOUY, Bertrand Guillaume Robin PELLATON, Josselin Luc Florent SICARD
  • TURBINE ROTOR FOR A GAS TURBINE ENGINE
    Publication number: 20170167264
    Abstract: A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.
    Type: Application
    Filed: May 7, 2015
    Publication date: June 15, 2017
    Inventors: Josselin Luc Florent SICARD, Bertrand PELLATON, Hélène Marie BARRET, Benoit Guillaume SILET, Anne-Flore Karine HOULET