Patents by Inventor Antoine Elie Hellegouarch
Antoine Elie Hellegouarch 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: 11738878Abstract: The invention concerns a suspension system (7) for a turbomachine, comprising a beam (10) intended to be attached to a pylon of an aircraft, and a cylindrical part (15) articulated on a ball joint housing, the ball joint housing comprising a body (11), and a ball joint nut (16) articulated on the body (11), the cylindrical part (15) being mounted so as to pivot about its axis in the ball joint nut, characterized in that the cylindrical part (15) is intended to be integral with a fixed part (8) of the turbomachine (1), the body (11) of the ball joint housing being integral with the beam (10).Type: GrantFiled: October 4, 2019Date of Patent: August 29, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Quentin Matthias Emmanuel Garnaud, Antoine Elie Hellegouarch
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Engine assembly for an aircraft having an air-oil exchanger system support with optimized attachment
Patent number: 11614033Abstract: An engine assembly for an aircraft including a bypass turbomachine as well as a turbomachine attachment pylon including an air-oil exchanger system arranged in an inter-ducts compartment between the flow ducts, the compartment being delimited radially on the outside by an inter-ducts cowling, the exchanger system being supplied with air from a secondary flow duct of the turbomachine delimited radially on the inside by the inter-ducts cowling, and the exchanger system being supported by a support arranged in the inter-ducts compartment, this support being mechanically connected to the attachment pylon by connecting means passing through the inter-ducts cowling.Type: GrantFiled: November 19, 2019Date of Patent: March 28, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Marc Patrick Tesniere -
Patent number: 11572833Abstract: An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.Type: GrantFiled: April 2, 2019Date of Patent: February 7, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Frédéric Paul Eichstadt, Quentin Matthias Emmanuel Garnaud
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Patent number: 11549462Abstract: A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.Type: GrantFiled: May 27, 2020Date of Patent: January 10, 2023Assignees: Safran Nacelles, SAFRAN AIRCRAFT ENGINESInventors: Sébastien Michel Thierry Guillemant, Pierre Caruel, Olivier Kerbler, Alexis Heau, Mathieu Lerouvreur, Antoine Elie Hellegouarch
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Patent number: 11542024Abstract: A load-bearing structure is configured to be mounted on an engine core of a turbofan engine. The load-bearing structure comprises two longitudinal beams and a transverse connection connecting them. Each of the longitudinal beams comprises a forward mounting interface and a rear mounting interface for mounting the structure on the engine core while allowing at least the longitudinal travel of the engine core. Each longitudinal beam also comprises a lateral suspension point for transmitting longitudinal and vertical forces between the load-bearing structure and a suspension structure. The load-bearing structure further comprises a transverse connection comprising a central suspension point for transmitting lateral and vertical forces between the load-bearing structure and the suspension structure.Type: GrantFiled: December 18, 2018Date of Patent: January 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Marc Patrick Tesniere
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Patent number: 11440670Abstract: The invention concerns a suspension device (4) for a turbomachine comprising a body (15) intended to be fixed to a fixed part of an aircraft, extending along a longitudinal axis (A) intended to be parallel to a driving shaft axis of the turbomachine once the suspension device (4) is connected to the turbomachine, a first connecting rod (28) and a second connecting rod (29) located in the same transverse plane (P) perpendicular to the longitudinal axis (A) of the body, each comprising a first end articulated with respect to the body (15), and a second end intended to be articulated to a first part of the turbomachine, a third connecting rod (37) articulated on the body (15) between the first ends of the first and second connecting rods (28, 29) and intended to be articulated on a first part of the turbomachine between the second ends of the first and second connecting rods (28, 29), the suspension device (4) being characterised in that it further comprises a rudder (45) articulated on the body (15) and a fourtType: GrantFiled: December 14, 2018Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Marc Patrick Tesniere
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Patent number: 11434017Abstract: The invention relates to the field of fairings of aircraft propulsion units, and more particularly to an assembly comprising a longitudinal beam (31) configured to be mounted on a lateral of a turbofan (7) engine core (11), oriented parallel to a longitudinal axis (X) of the turbofan (7), an opening fairing (18) cowl (50) of the engine core (11) and a deployment mechanism (60) mounted on the longitudinal beam (31) to move the opening cowl (50) between an open position and a closed position.Type: GrantFiled: December 18, 2018Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Quentin Matthias Emmanuel Garnaud, Marc Patrick Tesniere
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Publication number: 20220177149Abstract: An air inlet duct for a nacelle of an aircraft propulsion assembly includes an annular body and an annular air inlet lip with two coaxial annular walls, inner and outer, respectively. The inner wall defining a portion of an inner annular surface of the air inlet duct and the outer wall defining a portion of an outer annular surface of the air inlet duct. A control system translates the lip from a first position, in which the lip is attached to the body, to a second position, in which the lip is axially separated from the body. An annular row of grilles is translatably secured to the lip. The grilles are housed inside the body in the first position and extended from the body in order for an air flow entering the air inlet duct to pass therethrough in the second position.Type: ApplicationFiled: March 19, 2020Publication date: June 9, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Quentin Matthias Emmanuel GARNAUD, Antoine Elie HELLEGOUARCH, Nicolas Joseph SIRVIN
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Patent number: 11300076Abstract: A propulsion unit includes a nacelle, a turbojet engine, and a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the turbojet engine. The propulsion unit further includes actuators arranged around the annular duct and each actuator has a front end attached to the turbojet engine and a rear end which translates movable rear covers and gratings for opening, in the annular duct, radial passages which receive said gratings. The propulsion unit further has lifting points that are arranged around the annular duct for lifting the turbojet engine. At least one of the lifting points is formed on a beam for attaching an front end of an actuator.Type: GrantFiled: August 20, 2020Date of Patent: April 12, 2022Assignees: Safran Nacelles, Safran Aircraft EnginesInventors: Patrick Boileau, Quentin Garnaud, Antoine Elie Hellegouarch, Gina Ferrier
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ENGINE ASSEMBLY FOR AN AIRCRAFT HAVING AN AIR-OIL EXCHANGER SYSTEM SUPPORT WITH OPTIMIZED ATTACHMENT
Publication number: 20220010728Abstract: An engine assembly for an aircraft including a bypass turbomachine as well as a turbomachine attachment pylon including an air-oil exchanger system arranged in an inter-ducts compartment between the flow ducts, the compartment being delimited radially on the outside by an inter-ducts cowling, the exchanger system being supplied with air from a secondary flow duct of the turbomachine delimited radially on the inside by the inter-ducts cowling, and the exchanger system being supported by a support arranged in the inter-ducts compartment, this support being mechanically connected to the attachment pylon by connecting means passing through the inter-ducts cowling.Type: ApplicationFiled: November 19, 2019Publication date: January 13, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie HELLEGOUARCH, Marc Patrick TESNIERE -
Publication number: 20210380265Abstract: The invention concerns a suspension system (7) for a turbomachine, comprising a beam (10) intended to be attached to a pylon of an aircraft, and a cylindrical part (15) articulated on a ball joint housing, the ball joint housing comprising a body (11), and a ball joint nut (16) articulated on the body (11), the cylindrical part (15) being mounted so as to pivot about its axis in the ball joint nut, characterized in that the cylindrical part (15) is intended to be integral with a fixed part (8) of the turbomachine (1), the body (11) of the ball joint housing being integral with the beam (10).Type: ApplicationFiled: October 4, 2019Publication date: December 9, 2021Inventors: Quentin Matthias Emmanuel GARNAUD, Antoine Elie HELLEGOUARCH
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Patent number: 11131270Abstract: The turbojet includes, linking two of its parts as a main nacelle portion and a rear nacelle portion, a device which moves them relative to one another, for example in order to open a reverse gas thrust slot. The device includes a sleeve and two rods which are coaxial connected together by two screw links and two locking devices which may be engaged independently, such that the deployment of one of the rods results in the opening of the slot and the movement of the other rod, controlled by the same device, only occurs under specific turbojet maintenance circumstances.Type: GrantFiled: December 20, 2018Date of Patent: September 28, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Emmanuel Pierre Dimitri Patsouris, Quentin Matthias Emmanuel Garnaud, Antoine Elie Hellegouarch, Martial Alexandre Monseu, Clementine Charlotte Marie Mouton
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Publication number: 20210115852Abstract: An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.Type: ApplicationFiled: April 2, 2019Publication date: April 22, 2021Inventors: Antoine Elie HELLEGOUARCH, Frédéric Paul EICHSTADT, Quentin Matthias Emmanuel GARNAUD
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Publication number: 20210094695Abstract: The invention concerns a suspension device (4) for a turbomachine comprising a body (15) intended to be fixed to a fixed part of an aircraft, extending along a longitudinal axis (A) intended to be parallel to a driving shaft axis of the turbomachine once the suspension device (4) is connected to the turbomachine, a first connecting rod (28) and a second connecting rod (29) located in the same transverse plane (P) perpendicular to the longitudinal axis (A) of the body, each comprising a first end articulated with respect to the body (15), and a second end intended to be articulated to a first part of the turbomachine, a third connecting rod (37) articulated on the body (15) between the first ends of the first and second connecting rods (28, 29) and intended to be articulated on a first part of the turbomachine between the second ends of the first and second connecting rods (28, 29), the suspension device (4) being characterised in that it further comprises a rudder (45) articulated on the body (15) and a fourtType: ApplicationFiled: December 14, 2018Publication date: April 1, 2021Inventors: Antoine Elie HELLEGOUARCH, Marc Patrick TESNIERE
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Publication number: 20210086906Abstract: A load-bearing structure is configured to be mounted on an engine core of a turbofan engine. The load-bearing structure comprises two longitudinal beams and a transverse connection connecting them. Each of the longitudinal beams comprises a forward mounting interface and a rear mounting interface for mounting the structure on the engine core while allowing at least the longitudinal travel of the engine core. Each longitudinal beam also comprises a lateral suspension point for transmitting longitudinal and vertical forces between the load-bearing structure and a suspension structure. The load-bearing structure further comprises a transverse connection comprising a central suspension point for transmitting lateral and vertical forces between the load-bearing structure and the suspension structure.Type: ApplicationFiled: December 18, 2018Publication date: March 25, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie HELLEGOUARCH, Marc Patrick TESNIERE
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Publication number: 20210003096Abstract: A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.Type: ApplicationFiled: May 27, 2020Publication date: January 7, 2021Applicants: Safran Nacelles, Safran Aircraft EnginesInventors: Sébastien Michel Thierry GUILLEMANT, Pierre CARUEL, Olivier KERBLER, Olivier HEAU, Mathieu LEROUVREUR, Antoine Elie HELLEGOUARCH
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Publication number: 20200378341Abstract: A propulsion unit includes a nacelle, a turbojet engine, and a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the turbojet engine. The propulsion unit further includes actuators arranged around the annular duct and each actuator has a front end attached to the turbojet engine and a rear end which translates movable rear covers and gratings for opening, in the annular duct, radial passages which receive said gratings. The propulsion unit further has lifting points that are arranged around the annular duct for lifting the turbojet engine. At least one of the lifting points is formed on a beam for attaching an front end of an actuator.Type: ApplicationFiled: August 20, 2020Publication date: December 3, 2020Applicants: Safran Nacelles, Safran Aircraft EnginesInventors: Patrick BOILEAU, Quentin GARNAUD, Antoine Elie HELLEGOUARCH, Gina FERRIER
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Publication number: 20200377220Abstract: The invention relates to the field of fairings of aircraft propulsion units, and more particularly to an assembly comprising a longitudinal beam (31) configured to be mounted on a lateral of a turbofan (7) engine core (11), oriented parallel to a longitudinal axis (X) of the turbofan (7), an opening fairing (18) cowl (50) of the engine core (11) and a deployment mechanism (60) mounted on the longitudinal beam (31) to move the opening cowl (50) between an open position and a closed position.Type: ApplicationFiled: December 18, 2018Publication date: December 3, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie HELLEGOUARCH, Quentin Matthias Emmanuel GARNAUD, Marc Patrick TESNIERE
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Patent number: 10836500Abstract: An assembly between an aircraft structural pylon and an aircraft turbine engine is disclosed, with the assembly comprising a beam intended to be attached to the turbine engine and wherein a knuckle intended for the installation of a pad integral with the pylon is mounted, with the beam comprising suspension lugs each including a bore for the passage of a shaft intended to further go through a bore formed in the pylon to connect the beam with the pylon.Type: GrantFiled: October 26, 2017Date of Patent: November 17, 2020Assignee: Safran Aircraft EnginesInventors: Antoine Elie Hellegouarch, Marc Patrick Tesniere
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Patent number: 10562638Abstract: The invention relates to a cradle (10) for an aircraft turbopropeller engine (12) of a substantially axial orientation, comprising a front arch (16) and a rear arch (18) extending transversely relative to said axial direction (A), said arches (16, 18) being open at their lower ends and connected to each other by at least one axial longeron (34) extending between said arches (16, 18), characterised in that the longeron (34) is arranged in an upper portion of the cradle (10) and is formed in a single piece with the front arch (16).Type: GrantFiled: July 20, 2017Date of Patent: February 18, 2020Assignee: SAFRAN AIRCFRAFT ENGINESInventors: Frederic Paul Eichstadt, Nora El Ghannam, Romain Jean-Claude Ferrier, Antoine Elie Hellegouarch