Patents by Inventor Benjamin BULOT

Benjamin BULOT 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: 11598348
    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: Grant
    Filed: December 13, 2019
    Date of Patent: March 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Benjamin Bulot, Eddy Keomorakott Souryavongsa
  • Patent number: 11492968
    Abstract: A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.
    Type: Grant
    Filed: October 2, 2018
    Date of Patent: November 8, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benjamin Bulot, Pradeep Cojande, Eva Julie Lebeault
  • 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
  • Patent number: 11053810
    Abstract: The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4I) and a suction face platform portion (4E), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4I, 4E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11A, 11B) of the pressure face and suction face platform portions (4I, 4E) of the adjacent blades.
    Type: Grant
    Filed: December 7, 2017
    Date of Patent: July 6, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matthieu Pierre Michel Dubosc, Benjamin Bulot
  • Patent number: 10941667
    Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.
    Type: Grant
    Filed: October 30, 2018
    Date of Patent: March 9, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Claire Marie Figeureu, Eric Pierre Georges Lemarechal, Benjamin Bulot, Mathieu Simon Paul Gruber, Raphael Barrier, Cyril Polacsek
  • Patent number: 10844736
    Abstract: An assembly for a primary flow path of a double flow turbomachine extending along a longitudinal axis including a reduction gear, configured to drive a fan in rotation, a stator including a plurality of vanes for straightening the primary flow path, and an intermediate casing, positioned downstream of the stator, including structural arms with fairings passing through the primary flow path, wherein a fairing and one straightening vane are connected together within the primary flow path by a connecting surface, the fairing and the vane being positioned longitudinally substantially at the reduction gear.
    Type: Grant
    Filed: August 29, 2018
    Date of Patent: November 24, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benjamin Bulot, Guillaume Claude Robert Belmon, Eva Julie Lebeault
  • Publication number: 20200232393
    Abstract: A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.
    Type: Application
    Filed: October 2, 2018
    Publication date: July 23, 2020
    Inventors: Benjamin BULOT, Pradeep COJANDE, Eva Julie LEBEAULT
  • Patent number: 10655486
    Abstract: An assembly for a turbine engine or turbine engine test bed, including a hub defined about a longitudinal axis, a blade, including a blade root, extending in a radial direction to the longitudinal axis, the hub including a recess capable of receiving the blade root by insertion in the radial direction, wherein the recess includes a groove, the blade root including a groove, so that the two grooves are facing each other when the blade root is inserted into the recess, the assembly further includes a seal located in the two grooves.
    Type: Grant
    Filed: August 22, 2018
    Date of Patent: May 19, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benjamin Bulot, Claire Marie Figeureu
  • Publication number: 20200024990
    Abstract: An assembly for a primary flow path of a double flow turbomachine extending along a longitudinal axis including a reduction gear, configured to drive a fan in rotation, a stator including a plurality of vanes for straightening the primary flow path, and an intermediate casing, positioned downstream of the stator, including structural arms with fairings passing through the primary flow path, wherein a fairing and one straightening vane are connected together within the primary flow path by a connecting surface, the fairing and the vane being positioned longitudinally substantially at the reduction gear.
    Type: Application
    Filed: August 29, 2018
    Publication date: January 23, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Benjamin Bulot, Guillaume Claude Robert Belmon, Eva Julie Lebeault
  • Publication number: 20190170003
    Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.
    Type: Application
    Filed: October 30, 2018
    Publication date: June 6, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Claire Marie FIGEUREU, Eric Pierre Georges LEMARECHAL, Benjamin BULOT, Mathieu Simon Paul GRUBER, Raphael BARRIER, Cyril POLACSEK
  • Publication number: 20190063238
    Abstract: An assembly for a turbine engine or turbine engine test bed, including a hub defined about a longitudinal axis, a blade, including a blade root, extending in a radial direction to the longitudinal axis, the hub including a recess capable of receiving the blade root by insertion in the radial direction, wherein the recess includes a groove, the blade root including a groove, so that the two grooves are facing each other when the blade root is inserted into the recess, the assembly further includes a seal located in the two grooves.
    Type: Application
    Filed: August 22, 2018
    Publication date: February 28, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Benjamin BULOT, Claire Marie FIGEUREU
  • Publication number: 20180163556
    Abstract: The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4I) and a suction face platform portion (4E), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4I, 4E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11A, 11B) of the pressure face and suction face platform portions (4I, 4E) of the adjacent blades.
    Type: Application
    Filed: December 7, 2017
    Publication date: June 14, 2018
    Inventors: Matthieu Pierre Michel DUBOSC, Benjamin BULOT