Patents by Inventor Jérôme Corfa
Jérôme Corfa 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: 12158122Abstract: A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.Type: GrantFiled: December 21, 2022Date of Patent: December 3, 2024Assignee: SAFRAN NACELLESInventors: Romain Gardel, Pierre-Alain Reboul, Jérôme Corfa, Jean-Philippe Joret, Thomas Marlay, Matthieu Menielle
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Patent number: 11891965Abstract: A turbofan engine nacelle includes a thrust reverser system provided with at least one movable cowl retracting towards a rear reverse-jet position, tilting pivoting flaps which at least partially close an annular flow duct, and opening lateral openings of this annular flow duct equipped with reverser grids. Each movable cowl includes a control sector that slides in a transverse plane, a deflection device linking a fixed part of the nacelle to this control sector in order to make it slide towards a reversal position when the movable cowl retracts, and flap connecting rods linking this control sector to the pivoting flaps, which tilt these flaps, closing the annular flow duct, when the control sector slides towards its reversal position.Type: GrantFiled: March 18, 2021Date of Patent: February 6, 2024Assignee: Safran NacellesInventors: François Bellet, Jérôme Corfa, Julien Van Den Driessche
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Publication number: 20230192308Abstract: A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.Type: ApplicationFiled: December 21, 2022Publication date: June 22, 2023Inventors: Romain GARDEL, Pierre-Alain REBOUL, Jérôme CORFA, Jean-Philippe JORET, Thomas MARLAY, Matthieu MENIELLE
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Patent number: 11293378Abstract: A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.Type: GrantFiled: June 1, 2020Date of Patent: April 5, 2022Assignee: Safran NacellesInventors: Alexis Tabouret, Quentin Girardie, Jérôme Corfa, Matthieu Menielle, Fabrice Provost
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Publication number: 20210207558Abstract: A turbofan engine nacelle includes a thrust reverser system provided with at least one movable cowl retracting towards a rear reverse-jet position, tilting pivoting flaps which at least partially close an annular flow duct, and opening lateral openings of this annular flow duct equipped with reverser grids. Each movable cowl includes a control sector that slides in a transverse plane, a deflection device linking a fixed part of the nacelle to this control sector in order to make it slide towards a reversal position when the movable cowl retracts, and flap connecting rods linking this control sector to the pivoting flaps, which tilt these flaps, closing the annular flow duct, when the control sector slides towards its reversal position.Type: ApplicationFiled: March 18, 2021Publication date: July 8, 2021Applicant: Safran NacellesInventors: François BELLET, Jérôme CORFA, Julien VAN DEN DRIESSCHE
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Publication number: 20200291894Abstract: A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.Type: ApplicationFiled: June 1, 2020Publication date: September 17, 2020Applicant: Safran NacellesInventors: Alexis TABOURET, Quentin GIRARDIE, Jérôme CORFA, Mathieu MENIELLE, Fabrice PROVOST
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Patent number: 10753315Abstract: The present disclosure relates to a rear assembly of a turbojet engine nacelle that includes a thrust reverser fixed structure having at least one half-cowl mounted on a beam pivotally hinged by at least one hinge, a suspension mast on which the fixed structure is movably mounted, a hatch for access to the hinge of the half-cowl, and a fireproof sealing device which includes a sealing gasket adapted to provide sealing between a median section of the nacelle and the beam area. The sealing gasket includes a tubular gasket type lower portion which extends at least partially over a seal bearing edge of the half-cowl that is adapted to cooperate with a seal bearing wall of the mast and an upper portion including an elastically deformable sealing sheet extending from the seal bearing wall of the mast to the rear face of the hatch for access to the hinge.Type: GrantFiled: January 14, 2019Date of Patent: August 25, 2020Assignee: Safran NacellesInventors: Jean-Philippe Joret, Jérôme Corfa, Serge Bunel, Xavier Bouteiller
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Patent number: 10634059Abstract: An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.Type: GrantFiled: June 22, 2017Date of Patent: April 28, 2020Assignee: SAFRAN NACELLESInventors: Jean-Paul Rami, Jérôme Corfa, Marc Versaevel, François Brefort, Remko Moeys
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Publication number: 20200025135Abstract: The present disclosure relates to a rear assembly of a turbojet engine nacelle that includes a thrust reverser fixed structure having at least one half-cowl mounted on a beam pivotally hinged by at least one hinge, a suspension mast on which the fixed structure is movably mounted, a hatch for access to the hinge of the half-cowl, and a fireproof sealing device which includes a sealing gasket adapted to provide sealing between a median section of the nacelle and the beam area. The sealing gasket includes a tubular gasket type lower portion which extends at least partially over a seal bearing edge of the half-cowl that is adapted to cooperate with a seal bearing wall of the mast and an upper portion including an elastically deformable sealing sheet extending from the seal bearing wall of the mast to the rear face of the hatch for access to the hinge.Type: ApplicationFiled: January 14, 2019Publication date: January 23, 2020Applicant: Safran NacellesInventors: Jean-Philippe JORET, Jérôme CORFA, Serge BUNEL, Xavier BOUTEILLER
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Patent number: 10047634Abstract: An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.Type: GrantFiled: May 27, 2014Date of Patent: August 14, 2018Assignee: AIRCELLEInventors: Corentin Hue, Jérôme Corfa
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Publication number: 20170292453Abstract: An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.Type: ApplicationFiled: June 22, 2017Publication date: October 12, 2017Applicant: SAFRAN NACELLESInventors: Jean-Paul RAMI, Jérôme CORFA, Marc VERSAEVEL, François BREFORT, Remko MOEYS
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Publication number: 20160053720Abstract: The present disclosure provides a thrust reverser device for a nacelle of a by-pass turbojet engine, including: a cowl moving alternately between a deployed position in which the cowl opens a passage within the nacelle and a retracted position in which the cowl closes the passage; a locking/unlocking system to lock and unlock the cowl, the locking/unlocking system moving alternately between a closed position in which a bolt cooperates with a striker so as to hold the cowl in the retracted position, and an open position in which the bolt releases the striker, so as to allow a switching of the cowl from the retracted position to the deployed position; and a device for mechanically inhibiting the cowl from a movement, holding in the retracted position. In particular, the mechanical inhibition device holds the locking/unlocking system in the closed position.Type: ApplicationFiled: September 11, 2015Publication date: February 25, 2016Applicant: AIRCELLEInventors: Hazem KIOUA, Laurent Georges VALLEROY, Jerome LESCURE, Jerome CORFA
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Publication number: 20140271163Abstract: An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.Type: ApplicationFiled: May 27, 2014Publication date: September 18, 2014Applicant: AIRCELLEInventors: Corentin Hue, Jérôme Corfa