Patents by Inventor Guillaume Glemarec

Guillaume Glemarec 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).

  • Publication number: 20250243827
    Abstract: A multi-flow turbine engine for an aircraft, the turbine engine having a gas generator with geometrical characteristics allowing it to have at its periphery a cold compartment larger than its hot compartment.
    Type: Application
    Filed: April 15, 2022
    Publication date: July 31, 2025
    Applicants: SAFRAN AIRCRAFT ENGINES, GENERAL ELECTRIC COMPANY
    Inventors: Guillaume GLEMAREC, Valentin Sébastien Simon AVOYNE, Hélène Monique ORSI, Mathieu Marc Christian GAILLOT
  • Publication number: 20250215830
    Abstract: A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.
    Type: Application
    Filed: April 15, 2022
    Publication date: July 3, 2025
    Inventors: Guillaume GLEMAREC, Nicolas Maurice Herve AUSSEDAT, Pierre Charles CARUEL, Mathieu Marc Christian GAILLOT, Jean-Baptiste Manuel Nicolas VIGNES
  • Publication number: 20250206448
    Abstract: A suspension assembly for a turbine engine includes a beam that attaches to an aircraft pylon. The beam has first and second portions, each carrying a half-housing together defining a ball joint housing. A ball joint nut is hingedly engaged to rotate in the ball joint housing, and a cylindrical part is configured to be attached to a fixed portion of the turbine engine, hinged in the ball joint housing, and mounted so as to be pivotable about its axis in the ball joint nut. The suspension assembly further includes a support ring surrounding the two half-housings around their entire circumference. The support ring performs a safety function in the event of failure of at least one element of the suspension assembly.
    Type: Application
    Filed: March 27, 2023
    Publication date: June 26, 2025
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Valerio CAPASSO, Guillaume GLEMAREC, Jean-Baptiste Manuel Nicolas VIGNES
  • Publication number: 20250197016
    Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.
    Type: Application
    Filed: February 28, 2025
    Publication date: June 19, 2025
    Inventors: Michael Cline, Jonathan E. Coleman, Craig W. Higgins, Daniel E. Mollmann, Mark E. Linz, Guillaume Glemarec, Valerio Capasso, Jean-Baptiste Manuel Nicolas Vignes, Nicolas Maurice Hervé Aussedat, Francois Gallet
  • Patent number: 12296967
    Abstract: Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.
    Type: Grant
    Filed: January 13, 2022
    Date of Patent: May 13, 2025
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Glemarec, Jean-Baptiste Vignes, Romuald Muriel Gentils, Valerio Capasso
  • Patent number: 12246845
    Abstract: Methods, apparatus, systems and articles of manufacture for mounting a gas turbine engine are described. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.
    Type: Grant
    Filed: May 20, 2021
    Date of Patent: March 11, 2025
    Assignees: General Electric Company, Safran Aircraft Engines
    Inventors: Michael Cline, Jonathan E. Coleman, Craig W. Higgins, Daniel E. Mollmann, Mark E. Linz, Guillaume Glemarec, Valerio Capasso, Jean-Baptiste Manuel Nicolas Vignes, Nicolas Maurice Hervé Aussedat, Francois Gallet
  • Patent number: 12240618
    Abstract: A fan casing for an aircraft bypass turbojet engine includes one single wall configured to form at least one portion of an outer skin of a nacelle. The wall includes at least one reinforcement for stiffening the fan casing. The reinforcement is formed by a portion of the wall forming at least one annular area projecting towards an inside of the nacelle and/or having an overthickness. The reinforcement is further configured for fastening the fan casing to arms crossing a secondary stream flow path of the turbojet engine.
    Type: Grant
    Filed: December 13, 2021
    Date of Patent: March 4, 2025
    Assignee: Safran Aircraft Engines
    Inventors: Guillaume Glemarec, Quentin Matthias Emmanuel Garnaud, Frédéric Dautreppe
  • Publication number: 20240239502
    Abstract: A structure for linking and supporting a turbine engine on an aircraft pylon, the structure having a first longitudinal axis intended to extend parallel to a second longitudinal axis of the pylon, the structure including a first axial portion for fastening to the pylon, the first portion having an upper end that defines a substantially horizontal plane of interface with the pylon, and a lower end bearing suspension rods for suspending the turbine engine, which extend in a rear vertical plane; and a second axial portion that is intended to extend forward of the pylon and includes at least one suspension member of the turbine engine in a front vertical plane.
    Type: Application
    Filed: May 17, 2022
    Publication date: July 18, 2024
    Inventors: Guillaume GLEMAREC, Bruno Albert BEUTIN, Valerio CAPASSO, Jean-Baptiste Manuel Nicolas VIGNES
  • Patent number: 11970280
    Abstract: The invention relates to an assembly between an aircraft pylon (30) and a turbomachine (20) of longitudinal axis (X), the pylon (30) and the turbomachine (20) each comprising front and rear longitudinal regions, the assembly comprising a rear support (40) configured to connect the rear region of the turbomachine (20) to the rear region of the pylon (30), the assembly being characterized in that the rear support (40) comprises a sliding pivot connection arranged between the rear region of the turbomachine (20) and the rear region of the pylon (30), so as to allow the turbomachine (20) only translational and rotational movements along and about the longitudinal axis (X) and along and about a vertical axis (Z) and a rotational movement about a transverse axis (Y).
    Type: Grant
    Filed: January 5, 2021
    Date of Patent: April 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Glemarec, Guilhem Seize, Eric Francois Michel Maingre, Jean-Baptiste Vignes
  • Publication number: 20240052781
    Abstract: Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.
    Type: Application
    Filed: January 13, 2022
    Publication date: February 15, 2024
    Inventors: Guillaume GLEMAREC, Jean-Baptiste VIGNES, Romuald Muriel GENTILS, Valerio CAPASSO
  • Patent number: 11851201
    Abstract: The invention relates to a turbomachine (1) extending along an axis (X), comprising a high-pressure body with a high-pressure compressor (4) coupled in rotation to a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled in rotation to a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and means of suspension (12, 13) for the turbomachine (1), intended for attaching the turbomachine (1) to an aircraft pylon (11).
    Type: Grant
    Filed: October 4, 2019
    Date of Patent: December 26, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Quentin Matthias Emmanuel Garnaud, Guillaume Glemarec, Hervé Jean Albert Mouton, Guilhem Seize, Benoit Bernard René Leclerc
  • Publication number: 20230356853
    Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.
    Type: Application
    Filed: May 20, 2021
    Publication date: November 9, 2023
    Inventors: Michael Cline, Jonathan E. Coleman, Craig W. Higgins, Daniel E. Mollman, Mark E. Linz, Guillaume Glemarec, Valerio Capasso, Jean-Baptiste Manuel Nicolas Vignes, Nicolas Maurice Hervé Aussedat, Francois Gallet
  • Publication number: 20230358149
    Abstract: A turbine engine module of longitudinal axis X, including an unducted propeller intended to be rotated around the longitudinal axis X by a power shaft which is connected at least to a rotor member, at least one flow straightener including a plurality of stator vanes (28)-extending along a radial axis Z, at least one first casing mounted upstream, along the longitudinal axis, of the rotor member and a second casing mounted downstream, along the longitudinal axis, of the rotor member.
    Type: Application
    Filed: September 29, 2021
    Publication date: November 9, 2023
    Inventors: Paul Ghislain Albert LEVISSE, Olivier BELMONTE, Guillaume GLEMAREC
  • Patent number: 11732674
    Abstract: A nacelle for an aircraft bypass turbomachine, including: an annular envelope extending about a longitudinal axis, a thrust reverser including: an annular movable cowl situated downstream of the annular envelope and able to slide with respect to the annular envelope along the longitudinal axis between a closed position and an open position in which the cowl and the nacelle casing define an opening between one another, at least one first thrust reverser cascade, an actuating mechanism designed to allow a partial or total thrust-cancelling configuration of the thrust reverser, in which configuration the movable cowl is moved into its open position while maintaining the or each first cascade in its retracted position, the opening being occupied by at least one second thrust-attenuating cascade of the thrust reverser, in such a way that the secondary flow passing through the opening exits to the outside of the nacelle with a speed oriented so as to generate a substantially zero or positive thrust along the longit
    Type: Grant
    Filed: March 13, 2020
    Date of Patent: August 22, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Glemarec, Quentin Matthias Emmanuel Garnaud
  • Patent number: 11619191
    Abstract: A turbofan propulsion assembly includes a thrust reverser with movable flaps. The propulsion assembly further includes an engine and a nacelle surrounding the engine, and the nacelle includes a thrust reverser with sliding cowls and thrust reverser flaps, and an inner structure. The portion of the inner structure positioned perpendicular to the thrust reverser flaps includes two halves that can open toward the exterior of the nacelle cowls.
    Type: Grant
    Filed: September 18, 2020
    Date of Patent: April 4, 2023
    Assignees: Safran Nacelles, Safran Aircraft Engines
    Inventors: Quentin Garnaud, Guillaume Glemarec, Patrick Boileau, Ludovic Toupet
  • Publication number: 20230028982
    Abstract: The invention relates to an assembly between an aircraft pylon (30) and a turbomachine (20) of longitudinal axis (X), the pylon (30) and the turbomachine (20) each comprising front and rear longitudinal regions, the assembly comprising a rear support (40) configured to connect the rear region of the turbomachine (20) to the rear region of the pylon (30), the assembly being characterized in that the rear support (40) comprises a sliding pivot connection arranged between the rear region of the turbomachine (20) and the rear region of the pylon (30), so as to allow the turbomachine (20) only translational and rotational movements along and about the longitudinal axis (X) and along and about a vertical axis (Z) and a rotational movement about a transverse axis (Y).
    Type: Application
    Filed: January 5, 2021
    Publication date: January 26, 2023
    Inventors: Guillaume GLEMAREC, Guilhem SEIZE, Eric Francois Michel MAINGRE, Jean-Baptiste VIGNES
  • Publication number: 20220178330
    Abstract: A nacelle for an aircraft bypass turbomachine, including: an annular envelope extending about a longitudinal axis, a thrust reverser including: an annular movable cowl situated downstream of the annular envelope and able to slide with respect to the annular envelope along the longitudinal axis between a closed position and an open position in which the cowl and the nacelle casing define an opening between one another, at least one first thrust reverser cascade, an actuating mechanism designed to allow a partial or total thrust-cancelling configuration of the thrust reverser, in which configuration the movable cowl is moved into its open position while maintaining the or each first cascade in its retracted position, the opening being occupied by at least one second thrust-attenuating cascade of the thrust reverser, in such a way that the secondary flow passing through the opening exits to the outside of the nacelle with a speed oriented so as to generate a substantially zero or positive thrust along the longit
    Type: Application
    Filed: March 13, 2020
    Publication date: June 9, 2022
    Inventors: Guillaume GLEMAREC, Quentin Matthias Emmanuel GARNAUD
  • Publication number: 20220106049
    Abstract: A fan casing for an aircraft bypass turbojet engine includes one single wall configured to form at least one portion of an outer skin of a nacelle. The wall includes at least one reinforcement for stiffening the fan casing. The reinforcement is formed by a portion of the wall forming at least one annular area projecting towards an inside of the nacelle and/or having an overthickness. The reinforcement is further configured for fastening the fan casing to arms crossing a secondary stream flow path of the turbojet engine.
    Type: Application
    Filed: December 13, 2021
    Publication date: April 7, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume GLEMAREC, Quentin Matthias Emmanuel GARNAUD, Frédéric DAUTREPPE
  • Publication number: 20220082064
    Abstract: An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.
    Type: Application
    Filed: November 29, 2021
    Publication date: March 17, 2022
    Applicants: Safran Nacelles, SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick BOILEAU, Pierre CARUEL, Gina FERRIER, Quentin GARNAUD, Guillaume GLEMAREC
  • Publication number: 20210323690
    Abstract: The invention relates to a turbomachine (1) extending along an axis (X), comprising a high-pressure body with a high-pressure compressor (4) coupled in rotation to a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled in rotation to a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and means of suspension (12, 13) for the turbomachine (1), intended for attaching the turbomachine (1) to an aircraft pylon (11).
    Type: Application
    Filed: October 4, 2019
    Publication date: October 21, 2021
    Inventors: Quentin Matthias Emmanuel GARNAUD, Guillaume GLEMAREC, Hervé Jean Albert MOUTON, Guilhem SEIZE, Benoit Bernard Renée LECLERC