Patents Assigned to SAFRAN NACELLES
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Patent number: 12214893Abstract: An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.Type: GrantFiled: December 21, 2021Date of Patent: February 4, 2025Assignee: SAFRAN NACELLESInventors: Hazem Kioua, Thomas Marlay, Damien Lemoine, Ophélie Schmitter
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Publication number: 20250035069Abstract: An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.Type: ApplicationFiled: December 2, 2022Publication date: January 30, 2025Applicant: SAFRAN NACELLESInventors: Tony MIOSSEC, Fabien BRAVIN, Vincent DEVANLAY, Marc VERSAEVEL, Valentin SIMEON
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Patent number: 12208994Abstract: A handling assembly of a propulsion assembly includes a nacelle and an aircraft turbojet engine. The handling assembly also includes a handling envelope covering at least half of the circumference of an outer wall of an air inlet of the nacelle, when the propulsion assembly is mounted on said handling assembly, and at least two interfaces for attaching slings, the slings being connected to a hoisting system which is external to said handling assembly. A method for handling a propulsion assembly is also disclosed.Type: GrantFiled: March 1, 2021Date of Patent: January 28, 2025Assignee: Safran NacellesInventor: Patrick Boileau
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Patent number: 12208915Abstract: Aircraft having at least one propulsion unit supplied with hydrogen by at least one hydrogen tank, and having at least one thrust reversal system including at least one actuator. The aircraft can include at least one means for storing or transporting the residual hydrogen of the propulsion unit, a fuel cell disposed in the hydrogen power source and supplied with hydrogen by the at least one means for storing the residual hydrogen, and a hydrogen thrust reverser actuation system. The thrust reverser actuation system can include a hydrogen thrust reverser actuation controller and a hydrogen primary power unit with a fuel cell supplied with hydrogen and powering the at least one thrust reverser actuator.Type: GrantFiled: November 23, 2022Date of Patent: January 28, 2025Assignee: SAFRAN NACELLESInventors: Jihane Bellahbib, Hakim Maalioune
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Patent number: 12209554Abstract: A thrust reverser for an aircraft propulsion unit. The thrust reverser includes three gates that can be deployed downstream of an outlet section of the propulsion unit. The device increases the possibilities for installation of the reverser, in particular when a tail assembly extends in line with the propulsion unit.Type: GrantFiled: June 2, 2021Date of Patent: January 28, 2025Assignee: SAFRAN NACELLESInventors: Romain Gardel, Thomas Marlay, Matthieu Menielle, Ophélie Schmitter
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Patent number: 12209556Abstract: A thrust reverser includes a fixed structure and a movable structure defining an air stream, a flap including a single wall perforated on the surface thereof, and a structure strengthening the flap and having an acoustic function. The flap being articulated between the fixed structure and the movable structure to allow in a direct jet position, disposing the wall along an acoustic section of the movable structure and allowing the circulation of an air flow through the air stream, the acoustic section forming with the structure of the wall an acoustic resonator, and in a reverse jet position, disposing the wall to deflect an air flow passing through the air stream and allow the passage through the wall and through the air stream of a portion of the air flow deflected by the flap.Type: GrantFiled: June 7, 2021Date of Patent: January 28, 2025Assignee: Safran NacellesInventor: Romain Billault
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Publication number: 20250019081Abstract: An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.Type: ApplicationFiled: December 2, 2022Publication date: January 16, 2025Applicant: SAFRAN NACELLESInventors: Tony MIOSSEC, Fabien BRAVIN, Vincent DEVANLAY, Marc VERSAEVEL, Valentin SIMEON
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Patent number: 12188432Abstract: A device for attaching a connecting rod small end for a thrust reversal cascade flap onto a fixed internal structure of a turbojet engine nacelle includes a fitting configured to be fixed to the internal structure and a connection interface forming a joint between the connecting rod small end and the fitting. The device further includes a removable fork configured to cooperate with the connection interface, wherein the fork and the connection interface are arranged inside the fitting.Type: GrantFiled: February 5, 2021Date of Patent: January 7, 2025Assignee: SAFRAN NACELLESInventors: Xavier Cazuc, Jean-Phillipe Joret
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Publication number: 20250002167Abstract: A nacelle for an aircraft propulsion unit includes an air intake cowl, and an intermediate section including fixed and removable hoods defining an access space between front ends of the hoods and an outer rear end of the air intake cowl. The intermediate section includes an annular row of mutually spaced connecting parts which rigidly connect the outer rear end of the air intake cowl to the front ends of the hoods so as to transmit longitudinal forces, and an intermediate cowl extending between the air intake cowl and the hoods, around the connecting parts, thereby closing the access space and creating aerodynamic continuity with the air intake cowl and the hoods. The intermediate cowl is formed from at least one strip which is held in place by tangential clamping of the circumferential ends of the strip.Type: ApplicationFiled: September 12, 2022Publication date: January 2, 2025Applicant: SAFRAN NACELLESInventor: Pierre Charles CARUEL
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Patent number: 12180891Abstract: An acoustic panel for a turbine engine includes a first strip and a second strip each comprising an alternation of first ridges and second ridges connected by sidewalls. The first and second strips are joined to each other to form a plurality of cells, each delimited by a first ridge of the first strip and a first ridge of the second strip. A third strip is interposed between the first strip and the second strip and includes a first lateral wall bearing on the first strip The third strip further includes at least one tab that extends inside one of the cells and delimits all or part of a passage inside the associated cell.Type: GrantFiled: April 11, 2022Date of Patent: December 31, 2024Assignee: SAFRAN NACELLESInventors: Marc Versaevel, Bertrand Léon Marie Desjoyeaux, Pierre-Yves Gini
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Patent number: 12179918Abstract: A method for manufacturing a preform for producing a part made of composite material with an unchangeable final shape includes supplying a triaxial non-woven textile comprising a layer of fibers orientated in a first direction, a layer of fibers orientated in a second direction, a layer of fibers orientated in a third direction, and seams extending parallel to each other and forming sheaths for the circumferential fibers, arranging the textile on an element of unchangeable shape by placing the seams parallel to the circumferential direction of the element, and sliding the circumferential fibers into the sheaths so that the textile is in continuous contact with the element.Type: GrantFiled: March 1, 2021Date of Patent: December 31, 2024Assignee: Safran NacellesInventors: Bertrand Leon Marie Desjoyeaux, Julien Lorrillard, Benjamin Provost
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Patent number: 12173750Abstract: An aircraft propulsion assembly has a hinge for articulating a first and a second of its panels. The hinge includes a yoke rigidly connected to the first panel and a counter-yoke rigidly connected to the second panel, which is received between two lugs of the yoke. The yoke and the counter-yoke are passed through by a hinge pin that is movable between an extended position between the lugs of the yoke and a retracted position outside the yoke. The hinge further includes bayonet mounting means interposed between the pin and the yoke.Type: GrantFiled: April 2, 2021Date of Patent: December 24, 2024Assignee: SAFRAN NACELLESInventors: Philippe Avenel, Xavier Lore
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Publication number: 20240416597Abstract: Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.Type: ApplicationFiled: December 30, 2022Publication date: December 19, 2024Applicants: SAFRAN, SAFRAN NACELLESInventors: Patrick DUNLEAVY, Bertrand Léon Marie DESJOYEAUX
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Patent number: 12170077Abstract: An acoustic attenuation panel includes a perforated acoustic wall, a first honeycomb structure coupled to the perforated acoustic wall and including a plurality of acoustic cells defined by peripheral partitions, a second honeycomb structure including a plurality of acoustic cells defined by peripheral partitions, and a septum which includes a plurality of macro-perforations and is positioned between the first honeycomb structure and the second honeycomb structure. Each acoustic cell of the first honeycomb structure and each acoustic cell of the at least second honeycomb structure are arranged opposite a single perforation of the septum.Type: GrantFiled: April 8, 2022Date of Patent: December 17, 2024Assignee: Safran NacellesInventors: Marc Versaevel, Bertrand Desjoyeaux, Mathieu Preau
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Patent number: 12168964Abstract: A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.Type: GrantFiled: May 13, 2022Date of Patent: December 17, 2024Assignee: SAFRAN NACELLESInventors: Patrick Boileau, Julien Chandelier, Fabien Jourdan, Philippe Wiertel
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Publication number: 20240409222Abstract: A system (1) for cooling a refrigerant (R) for an aircraft comprising a plurality of ducts (2) for circulating the refrigerant (R) that are configured to be at least partially in contact with an airflow (A) so as to cool the refrigerant (R) through convection, the cooling system (1) comprising a safety heating device (3) extending internally inside at least one portion of the circulation ducts (2) so as to heat the refrigerant (R), a member (4) for measuring a physical parameter of the refrigerant (R) according to the flow rate of the refrigerant (R) in the circulation ducts (2) and a control member (5) configured to activate the safety heating device (3) when the measured physical parameter is below a predetermined threshold corresponding to a minimum flow rate of the refrigerant (R) in the circulation ducts (2).Type: ApplicationFiled: August 18, 2022Publication date: December 12, 2024Applicant: Safran NacellesInventor: Pierre Charles Caruel
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Patent number: 12163487Abstract: A structure comprising a nacelle or a thrust reverser, the structure comprising a stationary part and a movable part, the structure comprising: a first guide provided on or in the stationary part of the structure or the movable part of the structure; a first electrical connector attached to the stationary part of the structure: a second electrical connector attached to the movable part of the structure; and a carriage movable along the first guide: wherein the carriage comprises a closed loop electrical cable mounted in or on a carriage body such that the closed loop cable can rotate, wherein the first electrical connector is electrically connected to the closed loop electrical cable and the closed loop electrical cable is electrically connected to the second electrical connector, thereby providing an electrical connection from the stationary part of the structure to the movable part of the structure.Type: GrantFiled: August 15, 2019Date of Patent: December 10, 2024Assignee: SAFRAN NACELLES LIMITEDInventors: James Marquis, Patrick Gonidec, Stuart Hardyman, Loic Chapelain
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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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Publication number: 20240391206Abstract: A method for manufacturing a panel for a nacelle of an aircraft propulsion assembly includes: preparing mold elements each including lateral faces, an upper face, and a lower face; draping a material on a portion of the upper face and/or the lower face and at least one of the lateral faces of each of the mold elements to form at least one fold; and extracting the mold elements such that the at least one fold forms a cellular structure of the panel. The portion of the material on the upper face and/or the lower face forms a peripheral portion of the fold. The portion on the at least one of the lateral faces of each of the mold elements forms a central portion of the fold. The central portion is a portion of transverse partition walls of the panel, which define a plurality of cells.Type: ApplicationFiled: August 6, 2024Publication date: November 28, 2024Applicants: Safran Nacelles, Safran CeramicsInventors: Bertrand DESJOYEAUX, Davi Silva De Vasconcellos, Florent Bouillon, Arnaud Delehouze
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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