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公开(公告)号：US20220314558A1
公开(公告)日：2022-10-06
申请号：US17843224
申请日：2022-06-17
Applicant: Safran Nacelles
Inventor： Bertrand DESJOYEAUX , Mickaël SOREL , Franck MAZE , Géraldine OLIVEUX
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.
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公开(公告)号：US20210390940A1
公开(公告)日：2021-12-16
申请号：US17460933
申请日：2021-08-30
Applicant: Safran Nacelles
Inventor： Bertrand DESJOYEAUX , Marc VERSAEVEL , Mathieu PREAU , Laurent MOREAU
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.
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公开(公告)号：US20190039265A1
公开(公告)日：2019-02-07
申请号：US16155417
申请日：2018-10-09
Applicant: Safran Nacelles
Inventor： Bertrand DESJOYEAUX , Benjamin PROVOST , Sébastien LOUCHARD , Fabien DEPEUX
Abstract: The present disclosure relates to a preform that includes layers of textile reinforcements that are arranged in a mold by an automatic placement head and are connected to each other, and which can be dry or pre-impregnated, in order to form a part made of composite materials after curing of an impregnating resin. The part includes a folding produced by conformation of the preform after the placement of the layers of textile reinforcements. At the folding, there are spacings between at least some of the layers of textile reinforcements.
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公开(公告)号：US20240391206A1
公开(公告)日：2024-11-28
申请号：US18795709
申请日：2024-08-06
Applicant: Safran Nacelles , Safran Ceramics
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.
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公开(公告)号：US20240367355A1
公开(公告)日：2024-11-07
申请号：US18412753
申请日：2024-01-15
Applicant: Safran Nacelles
Inventor： Mathieu PREAU , Bertrand DESJOYEAUX , Franck MAZE , Mickaël SOREL
IPC: B29C43/50 , B29C43/02 , B29C43/36 , B29C70/46 , B29K105/08 , B29K307/04 , B29L31/30
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.
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Patent Agency Ranking
6.发明申请公开(公告)号：US20200300196A1
公开(公告)日：2020-09-24
申请号：US16800286
申请日：2020-02-25
Applicant: Safran Nacelles , Safran Ceramics
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.
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公开(公告)号：US20200180238A1
公开(公告)日：2020-06-11
申请号：US16785979
申请日：2020-02-10
Applicant: Safran Nacelles
Inventor： Bertrand DESJOYEAUX , Davi SILVA DE VASCONCELLOS , Benjamin PROVOST
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.
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公开(公告)号：US20170175308A1
公开(公告)日：2017-06-22
申请号：US15454022
申请日：2017-03-09
Applicant: SAFRAN NACELLES
Inventor： Benjamin PROVOST , Julien LORRILLARD , Bertrand DESJOYEAUX , Michel ROGNANT
CPC classification number: D03D25/005 , B29B11/16 , B29C70/24 , B29K2307/04 , D03J1/00 , D10B2505/02 , F01D5/282 , F01D9/00 , F01D9/04 , F01D25/24 , F01D25/243 , F01D25/246 , F01D25/265 , Y02T50/672
Abstract: The present disclosure concerns a preform for a curved composite stiffener for an axisymmetric part such as a shroud, including at least one web and at least one flange curved about an axis of revolution of the preform and defining a substantially “T” or an “I” shaped section. In one form, the preform includes a web and a flange, wherein the web includes a plurality of warp yarns circumferentially oriented relative to the axis of revolution of the preform, and a plurality of weft yarns oriented radially relative to said axis, and the flange includes a plurality of warp yarns circumferentially oriented relative to the axis of revolution of the preform, and a plurality of weft yarns substantially parallel to said axis.
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公开(公告)号：US20200180188A1
公开(公告)日：2020-06-11
申请号：US16793523
申请日：2020-02-18
Applicant: SAFRAN NACELLES
Inventor： Benjamin PROVOST , Bertrand DESJOYEAUX , Sébastien LOUCHARD , Fabien DEPEUX
Abstract: A method for manufacturing a preform has a non-developable end shape having, about a longitudinal axis (A), an end overall radius of curvature (R2), and, in at least a longitudinal section, curved segments forming bending radii linking straight segments. The method includes a step of depositing successive layers giving the preform an initial substantially rotational shape having, about the longitudinal axis (A), an initial overall radius of curvature, then a step of deploying the preform by increasing the initial overall radius of curvature until the end overall radius of curvature is reached (R2), in order to close the bending radii of the curved segments.
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公开(公告)号：US20200010206A1
公开(公告)日：2020-01-09
申请号：US16549359
申请日：2019-08-23
Applicant: Safran Nacelles
Inventor： Bertrand DESJOYEAUX , Sylvain SENTIS , Arnaud DELEHOUZE , François TAILLARD
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.
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