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).
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Patent number: 11970280Abstract: 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: GrantFiled: January 5, 2021Date of Patent: April 30, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Glemarec, Guilhem Seize, Eric Francois Michel Maingre, Jean-Baptiste Vignes
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Publication number: 20240052781Abstract: 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: ApplicationFiled: January 13, 2022Publication date: February 15, 2024Inventors: Guillaume GLEMAREC, Jean-Baptiste VIGNES, Romuald Muriel GENTILS, Valerio CAPASSO
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Patent number: 11851201Abstract: 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: GrantFiled: October 4, 2019Date of Patent: December 26, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Quentin Matthias Emmanuel Garnaud, Guillaume Glemarec, Hervé Jean Albert Mouton, Guilhem Seize, Benoit Bernard René Leclerc
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Publication number: 20230356853Abstract: 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: ApplicationFiled: May 20, 2021Publication date: November 9, 2023Inventors: 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
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Publication number: 20230358149Abstract: 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: ApplicationFiled: September 29, 2021Publication date: November 9, 2023Inventors: Paul Ghislain Albert LEVISSE, Olivier BELMONTE, Guillaume GLEMAREC
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Patent number: 11732674Abstract: 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 longitType: GrantFiled: March 13, 2020Date of Patent: August 22, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Glemarec, Quentin Matthias Emmanuel Garnaud
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Patent number: 11619191Abstract: 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: GrantFiled: September 18, 2020Date of Patent: April 4, 2023Assignees: Safran Nacelles, Safran Aircraft EnginesInventors: Quentin Garnaud, Guillaume Glemarec, Patrick Boileau, Ludovic Toupet
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Publication number: 20230028982Abstract: 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: ApplicationFiled: January 5, 2021Publication date: January 26, 2023Inventors: Guillaume GLEMAREC, Guilhem SEIZE, Eric Francois Michel MAINGRE, Jean-Baptiste VIGNES
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Publication number: 20220178330Abstract: 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 longitType: ApplicationFiled: March 13, 2020Publication date: June 9, 2022Inventors: Guillaume GLEMAREC, Quentin Matthias Emmanuel GARNAUD
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Publication number: 20220106049Abstract: 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: ApplicationFiled: December 13, 2021Publication date: April 7, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Guillaume GLEMAREC, Quentin Matthias Emmanuel GARNAUD, Frédéric DAUTREPPE
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Publication number: 20220082064Abstract: 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: ApplicationFiled: November 29, 2021Publication date: March 17, 2022Applicants: Safran Nacelles, SAFRAN AIRCRAFT ENGINESInventors: Patrick BOILEAU, Pierre CARUEL, Gina FERRIER, Quentin GARNAUD, Guillaume GLEMAREC
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Publication number: 20210323690Abstract: 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: ApplicationFiled: October 4, 2019Publication date: October 21, 2021Inventors: Quentin Matthias Emmanuel GARNAUD, Guillaume GLEMAREC, Hervé Jean Albert MOUTON, Guilhem SEIZE, Benoit Bernard Renée LECLERC
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Publication number: 20210003097Abstract: 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: ApplicationFiled: September 18, 2020Publication date: January 7, 2021Applicants: Safran Nacelles, Safran Aircraft EnginesInventors: Quentin GARNAUD, Guillaume GLEMAREC, Patrick BOILEAU, Ludovic TOUPET
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Patent number: 10428733Abstract: A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.Type: GrantFiled: October 14, 2014Date of Patent: October 1, 2019Assignees: SNECMA, SOCIETE LORRAINE DE CONSTRUCTION AERONAUTIQUEInventors: Mathieu Ange Poisson, Stéphane Orcel, Guillaume Glemarec, Jean-Luc Pacary
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Publication number: 20180230949Abstract: The present disclosure provides a variable section nozzle for an aircraft nacelle having a longitudinal axis. The variable section nozzle includes movable doors and at least one displacement device for displacing the movable doors between a reduced section position and a larger position. The movable doors include at least one first guide device and at least one second guide device, each operable to guide the displacement of the doors relative to a fixed structure of the nozzle. The second guide device is disposed downstream relative to the first guide device and each of the first and second guide devices provide a curvilinear path. In one form, the curvilinear paths are substantially circular and define a circular arc.Type: ApplicationFiled: April 13, 2018Publication date: August 16, 2018Applicant: Safran NacellesInventors: Olivier KERBLER, Loïc GRALL, Guillaume GLEMAREC, Amadéo GALASSO, José FAUGERAS, Mélody SERISET
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Publication number: 20160237898Abstract: A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.Type: ApplicationFiled: October 14, 2014Publication date: August 18, 2016Applicants: SNECMA, SOCIETE LORRAINE DE CONSTRUCTION AERONAUTIQUEInventors: Mathieu Ange Poisson, Stéphane Orcel, Guillaume Glemarec, Jean-Luc Pacary