Patents by Inventor Bertrand Desjoyeaux

Bertrand Desjoyeaux 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: 12170077
    Abstract: 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: Grant
    Filed: April 8, 2022
    Date of Patent: December 17, 2024
    Assignee: Safran Nacelles
    Inventors: Marc Versaevel, Bertrand Desjoyeaux, Mathieu Preau
  • Publication number: 20240391206
    Abstract: 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: Application
    Filed: August 6, 2024
    Publication date: November 28, 2024
    Applicants: Safran Nacelles, Safran Ceramics
    Inventors: Bertrand DESJOYEAUX, Davi Silva De Vasconcellos, Florent Bouillon, Arnaud Delehouze
  • Publication number: 20240367355
    Abstract: Tooling for manufacturing an air deflection cascade for a thrust reverser system of an aircraft nacelle includes a plurality of spars, each spar being connected to at least one adjacent spar by a plurality of deflection vanes. The tooling includes at least one molding bar and at least one molding column of a row of vanes, comprising two opposing lateral faces extending along the longitudinal direction of the tooling, and comprising molding cavities. The tooling includes a fixed structure on which the molding bar and the molding column are mounted. The fixed structure enabling a translational movement, along a transverse direction of the tooling, of the molding bar. The tooling includes a compression device to provide the compression of elements made of a composite material arranged in the tooling and intended to form at least one part of the cascade to be manufactured.
    Type: Application
    Filed: January 15, 2024
    Publication date: November 7, 2024
    Applicant: Safran Nacelles
    Inventors: Mathieu PREAU, Bertrand DESJOYEAUX, Franck MAZE, Mickaël SOREL
  • Patent number: 12122106
    Abstract: Tooling for manufacture of an apertured element made of a composite material includes first and second sole plates and tooling elements. Each sole plate is configured to be placed on either side of the apertured element to be manufactured. The tooling elements are placed between the first and second sole plates. The tooling elements include at least one core and peripheral bars. The core is configured to delimit a cell of the apertured element to be manufactured. The core is movable in translation along the first and second sole plates. The peripheral bars are placed on a periphery of the core and configured to delimit the apertured element to be manufactured. At least one peripheral bar is movable in translation along the first and second sole plates.
    Type: Grant
    Filed: June 17, 2022
    Date of Patent: October 22, 2024
    Assignee: Safran Nacelles
    Inventors: Bertrand Desjoyeaux, Mickaël Sorel, Franck Maze, Géraldine Oliveux
  • Patent number: 12090741
    Abstract: A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.
    Type: Grant
    Filed: February 25, 2020
    Date of Patent: September 17, 2024
    Assignees: Safran Nacelles, Safran Ceramics
    Inventors: Bertrand Desjoyeaux, Davi Silva De Vasconcellos, Florent Bouillon, Arnaud Delehouze
  • Patent number: 11932399
    Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.
    Type: Grant
    Filed: August 26, 2021
    Date of Patent: March 19, 2024
    Assignees: Safran Nacelles, Safran Ceramics
    Inventors: Bertrand Desjoyeaux, Davi Silva De Vasconcellos, François Taillard, Florent Bouillon
  • Patent number: 11686247
    Abstract: An acoustic panel with a cellular core includes cells that are provided with one or more obstacles, each of the obstacles extending transversely in relation to the main axis of the associated cell so as to increase the length of the path (F) that sound waves travel through the cell. Methods enabling the production of such a panel implements steps of cutting, folding and bonding that are suitable for creating cells provided with such obstacles.
    Type: Grant
    Filed: March 2, 2020
    Date of Patent: June 27, 2023
    Assignee: Safran Nacelles
    Inventors: Bertrand Desjoyeaux, Marc Versaevel
  • Patent number: 11655044
    Abstract: An rear fairing for a pylon supporting an aircraft turbojet engine forms an aerodynamic surface covering the base of the pylon. The rear fairing is elongated in a longitudinal direction and includes a floor arranged opposite the hot gases exiting the turbojet engine and side walls constituting aerodynamic surfaces. The floor and the side walls include ceramic matrix composite materials made from preforms formed by layers of superimposed warp and weft yarns, the preforms have interlayer weaving yarns connecting the layers to one another.
    Type: Grant
    Filed: August 23, 2019
    Date of Patent: May 23, 2023
    Assignee: Safran Nacelles
    Inventors: Bertrand Desjoyeaux, Sylvain Sentis, Arnaud Delehouze, François Taillard
  • Patent number: 11512666
    Abstract: A structure for the nacelle of an aircraft propulsion unit includes a first skin and stiffeners arranged to hold acoustic treatment modules against the first skin. Each acoustic treatment module includes a honeycomb core and a second skin, such that the honeycomb core is sandwiched between the first skin and the second skin. Such a structure allows the structural reinforcement function provided by the stiffeners to be separated from the acoustic treatment function performed by the acoustic treatment modules which are simply bearing on the first skin.
    Type: Grant
    Filed: July 6, 2020
    Date of Patent: November 29, 2022
    Assignees: Safan Nacelles, Safran Ceramics
    Inventors: Florent Bouillon, Franck Dupe, Benoît Carrere, Bertrand Desjoyeaux
  • Patent number: 11506144
    Abstract: A thrust reverser cascade for an aircraft nacelle includes a plurality of blades having a first and a second surface, the blades being connected to members connected to attachment flanges for attaching the thrust reverser cascade to the nacelle. At least one of the surfaces of the blades is covered with at least one layer of fibers, each layer including a plurality of fiber pieces which are pre-impregnated with resin. The fiber pieces are superimposed on one another, positioned parallel to the aerodynamic surface of the blade and oriented in different directions.
    Type: Grant
    Filed: February 7, 2020
    Date of Patent: November 22, 2022
    Assignees: Safran Nacelles, Safran
    Inventors: Géraldine Oliveux, Bertrand Desjoyeaux, Cedric Thomas
  • Patent number: 11472133
    Abstract: A method for manufacturing a fibrous tubular structure including lobes, in which fibers are draped/deposited on a mandrel having a shape corresponding to that of the fibrous structure, includes draping/deposition carried out such that at least one group of fibers has a same orientation with respect to the axis (A) of said fibrous structure, then, the fibers having been draped over an angular sector less than the total periphery of the mandrel, one of the ends of the fibrous structure is separated from the mandrel in order to allow the continuation of the draping on the same mandrel.
    Type: Grant
    Filed: February 10, 2020
    Date of Patent: October 18, 2022
    Assignee: Safran Nacelles
    Inventors: Bertrand Desjoyeaux, Davi Silva De Vasconcellos, Benjamin Provost
  • Patent number: 11473225
    Abstract: A method of manufacturing a preform including a core and a sole includes contour weaving the preform on a lap roller having a groove or an outgrowth allowing shape weaving of the core and the sole of the preform. At least one portion of the core and at least one portion of the sole include weft yarns which cross each other on common warp yarns.
    Type: Grant
    Filed: December 7, 2018
    Date of Patent: October 18, 2022
    Assignee: Safran Nacelles
    Inventors: Julien Lorrillard, Bertrand Desjoyeaux, Michel Rognant, Benjamin Provost
  • Publication number: 20220314558
    Abstract: Tooling for manufacture of an apertured element made of a composite material includes first and second sole plates and tooling elements. Each sole plate is configured to be placed on either side of the apertured element to be manufactured. The tooling elements are placed between the first and second sole plates. The tooling elements include at least one core and peripheral bars. The core is configured to delimit a cell of the apertured element to be manufactured. The core is movable in translation along the first and second sole plates. The peripheral bars are placed on a periphery of the core and configured to delimit the apertured element to be manufactured. At least one peripheral bar is movable in translation along the first and second sole plates.
    Type: Application
    Filed: June 17, 2022
    Publication date: October 6, 2022
    Applicant: Safran Nacelles
    Inventors: Bertrand DESJOYEAUX, Mickaël SOREL, Franck MAZE, Géraldine OLIVEUX
  • Patent number: 11427299
    Abstract: The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.
    Type: Grant
    Filed: February 25, 2020
    Date of Patent: August 30, 2022
    Assignees: Safran Nacelles, Safran Ceramics
    Inventors: Bertrand Desjoyeaux, Davi Silva De Vasconcellos, Florent Bouillon, Arnaud Delehouze
  • Publication number: 20220250767
    Abstract: An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.
    Type: Application
    Filed: April 26, 2022
    Publication date: August 11, 2022
    Applicant: Safran Nacelles
    Inventors: Pierre CARUEL, Bertrand DESJOYEAUX, Bertrand LEROYER, Marc VERSAEVEL, Laurent Georges VALLEROY
  • Publication number: 20220230613
    Abstract: 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: Application
    Filed: April 8, 2022
    Publication date: July 21, 2022
    Applicant: Safran Nacelles
    Inventors: Marc VERSAEVEL, Bertrand DESJOYEAUX, Mathieu PREAU
  • Publication number: 20220042454
    Abstract: An air intake of a turbojet engine nacelle includes an annular structure including an outer fairing defining an aerodynamic outer surface and an inner fairing defining an aerodynamic inner surface. The outer and inner fairings are connected upstream by an air intake lip forming a leading edge. The inner fairing includes an outer skin fixed to the air intake lip by an upstream fixation flange, and the outer skin is configured to be fixed to an outer fan casing by a downstream fixation flange. The air intake includes at least one independent acoustic panel attached to the outer skin and which includes a perforated acoustic skin and a cellular core.
    Type: Application
    Filed: October 26, 2021
    Publication date: February 10, 2022
    Applicant: Safran Nacelles
    Inventors: Pierre CARUEL, Bertrand DESJOYEAUX, Bertrand LEROYER, Marc VERSAEVEL, Laurent Georges VALLEROY
  • Patent number: 11235492
    Abstract: A tubular structure having lobes is produced as a single piece over at least two lobes. Circumferential fibres of the structure have a constant orientation with respect to the longitudinal axis (A) of the structure in any plane (P) transverse to the longitudinal axis. The structure is obtained by weaving or by filament winding.
    Type: Grant
    Filed: November 25, 2019
    Date of Patent: February 1, 2022
    Assignee: Safran Nacelles
    Inventors: Bertrand Desjoyeaux, Benjamin Provost, Fabien Depeux, Davi Silva De Vasconcellos
  • Publication number: 20210390940
    Abstract: A method for manufacturing a sound attenuating panel uses an alveolar-core structure including a first edge and a second edge separated by alveolar cells, the alveolar cells including walls extending from the first and second edges and defining a primary conduit for the circulation of a sound wave that is to be attenuated. The method includes covering the first edge or the second edge of the alveolar-core structure with a compartmentation wall; deforming the compartmentation wall to define at least one secondary conduit for the circulation of a sound wave that is to be attenuated, the secondary conduit extending at least partially within said primary conduit; and creating an opening in the compartmentation wall to permit communication between the primary and secondary conduits.
    Type: Application
    Filed: August 30, 2021
    Publication date: December 16, 2021
    Applicant: Safran Nacelles
    Inventors: Bertrand DESJOYEAUX, Marc VERSAEVEL, Mathieu PREAU, Laurent MOREAU
  • Publication number: 20210380220
    Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.
    Type: Application
    Filed: August 26, 2021
    Publication date: December 9, 2021
    Applicants: Safran Nacelles, SAFRAN CERAMICS
    Inventors: Bertrand DESJOYEAUX, Davi SILVA DE VASCONCELLOS, François TAILLARD, Florent BOUILLON