Patents by Inventor Jean-Philippe Joret
Jean-Philippe Joret 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: 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
-
Patent number: 12152552Abstract: The invention relates to an assembly (601) which comprises a front frame (602) of a thrust reverser structure of an aircraft nacelle and at least one cascade (603). The assembly is characterized in that, when the cascade is fixed to the frame, the axial distance (L) that separates the first blading (605) upstream of the cascade from a covering area (606) between the extension of the cascade and the front frame is greater than or equal to once the mean height (h) of the cascade.Type: GrantFiled: February 16, 2021Date of Patent: November 26, 2024Assignee: SAFRAN NACELLESInventors: Xavier Cazuc, Vincent Jean-Francois Peyron, Jean-Philippe Joret, Sebastien Laurent Marie Pascal
-
Patent number: 12116954Abstract: The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising: an exhaust cone (100) comprising an outer annular wall (102) for the flow of a primary airflow and an annular box arranged radially inside said outer annular wall (102), the annular box comprising an inner annular wall (104) arranged radially inside the outer annular wall of the exhaust cone, an exhaust case arranged upstream of the exhaust cone, and a connecting member (106) flexible in a radial direction, interposed longitudinally between the exhaust case and the exhaust cone (100), the connecting member being fastened to the exhaust case and to the inner annular wall (104), and wherein the inner annular wall (104) is connected to the outer annular wall (102) by fastening means (112) configured to enable movements of the inner annular wall (104) in a circumferential direction and a longitudinal direction with respect to the outer annular wall (102).Type: GrantFiled: November 3, 2021Date of Patent: October 15, 2024Assignee: SAFRAN NACELLESInventors: Jean-Philippe Joret, Vincent Devanlay, Fabien Bravin, Boualem Merabet
-
Publication number: 20240317415Abstract: A propulsion unit includes a fairing delimiting a flow conduit for a secondary flow. This fairing comprises includes panels, at least one of which is articulated on a mast via connecting members such as clevises.Type: ApplicationFiled: June 27, 2022Publication date: September 26, 2024Inventors: Patrick André BOILEAU, Gérard CLERE, Jean-Philippe JORET
-
Publication number: 20240300661Abstract: A locking system for an aircraft nacelle is provided. The locking system includes a first portion configured to be mounted on a first part of an aircraft nacelle, and a second portion configured to be mounted on a second part of the aircraft nacelle. The locking system can be configured such that, when it is in the closed position, the first portion and the second portion are held together. The locking system further includes at least one buffer part and a load sensor joined together and configured to compress the load sensor between the buffer part and another part of the locking system when the locking system is in the closed position.Type: ApplicationFiled: June 27, 2022Publication date: September 12, 2024Applicant: SAFRAN NACELLESInventors: Jean-Philippe JORET, Vincent DUTOT, Stéphane RIQUIER, François BELLET, Charles-Antoine LAMPAERT
-
Publication number: 20240253804Abstract: An air ejection nozzle for a nacelle includes an outer aerodynamic line and an inner aerodynamic line meeting at a trailing edge. The air ejection nozzle includes at discrete positions at least one area of larger thickness that is compensated by at least one fairing to connect the aerodynamic lines to form the trailing edge. The fairing includes an outer wall and an inner wall delimiting a cavity therebetween. The inner wall provides for the continuity of the inner aerodynamic line, and the outer wall is solid and the inner wall is pierced so that the at least one fairing forms an acoustic attenuation structure.Type: ApplicationFiled: April 5, 2024Publication date: August 1, 2024Applicant: Safran NacellesInventors: Vincent DUTOT, Jean-Philippe Joret, Marc Versaevel, Vincent Lefeuvre
-
Patent number: 12049853Abstract: A thrust reverser for an aircraft bypass turbojet engine nacelle has a generally annular shape around an axis and includes an annular frame for securing deflection grids. The frame has a first frusto-conical wall widening in the downstream direction and including an upstream peripheral edge configured to be attached to a casing of the turbojet engine. A downstream peripheral edge of the wall extends in the continuation of the wall and secures the upstream ends of the grids. A second annular wall extends radially outwards from an outer frusto-conical face of the first wall. The first and second walls are integrally formed and the second wall has axial openings through which actuators pass.Type: GrantFiled: May 17, 2021Date of Patent: July 30, 2024Assignee: SAFRAN NACELLESInventors: Xavier Cazuc, Jean-Philippe Joret, Vincent Jean-François Peyron, Sébastien Laurent Marie Pascal
-
Patent number: 12044168Abstract: Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.Type: GrantFiled: October 1, 2021Date of Patent: July 23, 2024Assignee: SAFRAN NACELLESInventors: Hazem Kioua, Pierre Charles Caruel, Jean-Philippe Joret, Charles-Antoine Lampaert
-
Patent number: 12037941Abstract: Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.Type: GrantFiled: October 1, 2021Date of Patent: July 16, 2024Assignee: SAFRAN NACELLESInventors: Jean-Philippe Joret, Damien Lemoine, Charles-Antoine Lampaert, Hazem Kioua
-
Patent number: 12037940Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: •? pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •? a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •? at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •? at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.Type: GrantFiled: October 1, 2021Date of Patent: July 16, 2024Assignee: SAFRAN NACELLESInventors: Jean-Philippe Joret, Hazem Kioua, Emmanuel Lesteven
-
Patent number: 12000300Abstract: The invention relates to an assembly for a turbomachine, comprising an exhaust cone (18) and an exhaust case having an annular inner shell, the exhaust cone (18) and the exhaust case extending about an axis (X), the exhaust cone (18) having a radially outer skin (31) extending in the projection of said inner shell and a radially inner skin (30) defining a chamber (32) with the outer skin (31), the upstream end (33) of the cone (18) being fastened to the inner shell (19) via connecting lugs (39), the assembly comprising an annular fairing (29) located radially outside said lugs (39) and extending axially between the inner shell (19) of the exhaust case (17) and the outer skin (31) of the exhaust cone (18), said fairing (29) extending in the projection of said inner shell (19) and of the outer skin (31), the assembly being characterized in that the fairing (29) is segmented and consists of multiple angular segments (42) arranged circumferentially end to end.Type: GrantFiled: November 3, 2021Date of Patent: June 4, 2024Assignee: SAFRAN NACELLESInventors: Jean-Philippe Joret, Vincent Devanlay, Marine Ollivier, Guillaume Levieux
-
Patent number: 11959437Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.Type: GrantFiled: November 3, 2021Date of Patent: April 16, 2024Assignees: SAFRAN NACELLES, SAFRAN CERAMICSInventors: Jean-Philippe Joret, Vincent Devanlay, Fabien Bravin, Thomas Vandellos
-
Patent number: 11891185Abstract: A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.Type: GrantFiled: May 18, 2021Date of Patent: February 6, 2024Assignee: SAFRAN NACELLESInventors: Patrick André Boileau, Jean-Philippe Joret, Vincent Jean-François Peyron, Gina Ferrier
-
Publication number: 20240018902Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: a pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, a speed reducer fixedly mounted inside the pipe along the longitudinal axis, at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.Type: ApplicationFiled: October 1, 2021Publication date: January 18, 2024Applicant: SAFRAN NACELLESInventors: Jean-Philippe Joret, Hazem Kioua, Emmanuel Lesteven
-
Publication number: 20240018903Abstract: Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.Type: ApplicationFiled: October 1, 2021Publication date: January 18, 2024Applicant: SAFRAN NACELLESInventors: Jean-Philippe Joret, Damien Lemoine, Charles-Antoine Lampaert, Hazem Kioua
-
Publication number: 20240011453Abstract: The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising: an exhaust cone (100) comprising an outer annular wall (102) for the flow of a primary airflow and an annular box arranged radially inside said outer annular wall (102), the annular box comprising an inner annular wall (104) arranged radially inside the outer annular wall of the exhaust cone, an exhaust case arranged upstream of the exhaust cone, and a connecting member (106) flexible in a radial direction, interposed longitudinally between the exhaust case and the exhaust cone (100), the connecting member being fastened to the exhaust case and to the inner annular wall (104), and wherein the inner annular wall (104) is connected to the outer annular wall (102) by fastening means (112) configured to enable movements of the inner annular wall (104) in a circumferential direction and a longitudinal direction with respect to the outer annular wall (102).Type: ApplicationFiled: November 3, 2021Publication date: January 11, 2024Inventors: Jean-Philippe JORET, Vincent DEVANLAY, Fabien BRAVIN, Boualem MERABET
-
Publication number: 20240003315Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.Type: ApplicationFiled: November 3, 2021Publication date: January 4, 2024Applicants: SAFRAN NACELLES, SAFRAN CERAMICSInventors: Jean-Philippe JORET, Vincent DEVANLAY, Fabien BRAVIN, Thomas VANDELLOS
-
Publication number: 20230417182Abstract: Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.Type: ApplicationFiled: October 1, 2021Publication date: December 28, 2023Applicant: SAFRAN NACELLESInventors: Hazem Kioua, Pierre Charles Caruel, Jean-Philippe Joret, Charles-Antoine Lampaert
-
Publication number: 20230407814Abstract: An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.Type: ApplicationFiled: November 4, 2021Publication date: December 21, 2023Inventors: Thomas VANDELLOS, Benoit CARRERE, Eric CONETE, Jean-Philippe JORET, Vincent DEVANLAY, Clément Marie Benoît ROUSSILLE
-
Publication number: 20230407813Abstract: An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.Type: ApplicationFiled: November 3, 2021Publication date: December 21, 2023Applicant: SAFRAN NACELLESInventors: Jean-Philippe JORET, Vincent DEVANLAY, Fabien BRAVIN, Hélène MALOT