公开(公告)号：US20250019081A1

公开(公告)日：2025-01-16

申请号：US18714334

申请日：2022-12-02

Applicant: SAFRAN NACELLES

Inventor： Tony MIOSSEC ,  Fabien BRAVIN ,  Vincent DEVANLAY ,  Marc VERSAEVEL ,  Valentin SIMEON

IPC: B64D27/10

Abstract: 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.

公开(公告)号：US20250035069A1

公开(公告)日：2025-01-30

申请号：US18714363

申请日：2022-12-02

Applicant: SAFRAN NACELLES

Inventor： Tony MIOSSEC ,  Fabien BRAVIN ,  Vincent DEVANLAY ,  Marc VERSAEVEL ,  Valentin SIMEON

IPC: F02K1/82

Abstract: 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.

公开(公告)号：US20190264614A1

公开(公告)日：2019-08-29

申请号：US16411199

申请日：2019-05-14

Applicant: SAFRAN ,  Safran Nacelles

Inventor： Marc VERSAEVEL ,  Jean-Philippe GINEFRI ,  Fabrice PROVOST ,  Jeremy QUESNEL ,  Wouter BALK ,  Sébastien LOUCHARD ,  Loïc Hervé André LE BOULICAUT

IPC: F02C7/24 ,  B29D24/00 ,  G10K11/172

Abstract: An acoustic attenuation panel for a propulsion assembly includes an acoustic front skin having perforations, and a central structure formed from partitions arranged perpendicularly in order to make up cells, wherein the front skin and the central structure form the panel which is made as a single piece and is provided for directly covering a surface of an element of the propulsion assembly forming a rear skin which closes the cells of the central structure at the rear.

公开(公告)号：US20190161200A1

公开(公告)日：2019-05-30

申请号：US16260972

申请日：2019-01-29

Applicant: Safran Nacelles ,  Safran Aircraft Engines

Inventor： Marc VERSAEVEL ,  Denis RAMAGE ,  Baptiste CORDIER ,  Georges RIOU ,  Jacky MARDJONO

IPC: B64D33/02 ,  F02C7/045 ,  F02C7/24 ,  F02K1/82 ,  B64D29/00

Abstract: An acoustic attenuation panel for a propulsion unit including a nacelle and a turbojet engine includes a cellular core disposed between an inner skin and an outer skin, called acoustic skin, the acoustic skin including a plurality of acoustic apertures, the acoustic apertures being inclined, at a non-zero inclination angle (β) relative to the direction normal to the acoustic skin, upstream with respect to the flow direction of the air or gas flow to which the panel is intended to be subjected under normal operating conditions, that is to say upstream of the propulsion unit when the panel is mounted in such a unit.

公开(公告)号：US20170292453A1

公开(公告)日：2017-10-12

申请号：US15630223

申请日：2017-06-22

Applicant: SAFRAN NACELLES

Inventor： Jean-Paul RAMI ,  Jérôme CORFA ,  Marc VERSAEVEL ,  François BREFORT ,  Remko MOEYS

IPC: F02C7/24 ,  F02K1/82 ,  F02C7/045

CPC classification number: F02C7/24 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0206 ,  F02C7/045 ,  F02K1/827 ,  F04D29/665 ,  F05D2220/323 ,  F05D2250/191 ,  F05D2250/25 ,  F05D2250/283 ,  G10K11/172 ,  Y02T50/672

Abstract: 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.

公开(公告)号：US20240359421A1

公开(公告)日：2024-10-31

申请号：US18686592

申请日：2022-08-29

Applicant: SAFRAN NACELLES

Inventor： Marc VERSAEVEL ,  Pierre-Yves GINI ,  Hugo BOISTELLE ,  Bertrand Léon Marie DESJOYEAUX

IPC: B32B3/30 ,  B29C35/02 ,  B29C65/70 ,  B29C70/44 ,  B29K63/00 ,  B29K105/08 ,  B29K105/20 ,  B29K307/04 ,  B29K705/02 ,  B29L31/38 ,  B32B3/26 ,  B32B5/02 ,  B32B7/12 ,  B32B15/14 ,  B32B15/20

CPC classification number: B32B3/30 ,  B29C35/0227 ,  B29C65/70 ,  B29C70/44 ,  B32B3/266 ,  B32B5/02 ,  B32B7/12 ,  B32B15/14 ,  B32B15/20 ,  B29K2063/00 ,  B29K2105/08 ,  B29K2105/20 ,  B29K2307/04 ,  B29K2705/02 ,  B29K2995/0063 ,  B29K2995/0097 ,  B29L2031/38 ,  B32B2250/40 ,  B32B2255/02 ,  B32B2255/26 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/106 ,  B32B2307/102 ,  B32B2307/72 ,  B32B2605/18

Abstract: A method for manufacturing an acoustic panel including a first skin, a second skin and an intermediate structure enclosed between these skins and forming oblique cavities with respect to the latter. The method includes an intermediate polymerization step for fastening the intermediate structure to the first skin in order to increase the compressive strength thereof and in particular to support an automated operation of draping the second skin.

公开(公告)号：US20230003176A1

公开(公告)日：2023-01-05

申请号：US17903359

申请日：2022-09-06

Applicant: Safran Nacelles

Inventor： Bertrand Léon Marie DESJOYEAUX ,  Marc VERSAEVEL ,  Mathieu François Eric PREAU ,  Laurent MOREAU

IPC: F02K1/82 ,  B64D33/02

Abstract: A method for manufacturing an alveolar core structure includes at least one cell including a secondary duct having a first end defining a sound wave inlet, and an opposite second end, the secondary duct comprising a sound wave outlet. The method also includes a fastening step in which adhesive tapes transverse to the longitudinal direction of said first plate are applied on a first longitudinal plate. The secondary duct in the form of a flattened element is fastened, on the first plate, by gluing at its sound wave inlet. A second plate is applied. A step of deploying the first and second plates so as to form the peripheral wall of the cells and so that the flattened element is deployed.

公开(公告)号：US20220230613A1

公开(公告)日：2022-07-21

申请号：US17716089

申请日：2022-04-08

Applicant: Safran Nacelles

Inventor： Marc VERSAEVEL ,  Bertrand DESJOYEAUX ,  Mathieu PREAU

IPC: G10K11/172 ,  B64D33/02

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.

公开(公告)号：US20200309029A1

公开(公告)日：2020-10-01

申请号：US16901733

申请日：2020-06-15

Applicant: Safran Nacelles

Inventor： Patrick BOILEAU ,  Caroline COAT-LENZOTTI ,  Marc VERSAEVEL ,  Virginie Emmanuelle Anne Marie DIGEOS ,  Pierre-François BEHAGHEL

IPC: F02C7/047 ,  B64C7/02 ,  F02C7/045

Abstract: An air inflow lip of a nacelle for a turbojet of an aircraft, including a cavity defined by a leading edge of the nacelle and by an annular wall, includes an inner wall, an acoustic treatment device, and a pneumatic de-icing device including a de-icing fluid supply device. The inner wall of the air inflow lip includes acoustic boreholes and the pneumatic de-icing device includes a honeycombed de-icing plate mounted inside the cavity on the inner wall of the air inflow lip. Also included are conduits for the circulation of a de-icing fluid and acoustic wells communicating with the acoustic boreholes.

公开(公告)号：US20250001508A1

公开(公告)日：2025-01-02

申请号：US18757348

申请日：2024-06-27

Applicant: SAFRAN NACELLES

Inventor： Pierre-Yves GINI ,  Marc VERSAEVEL ,  Denis RAMAGE

IPC: B23B47/28 ,  B23B35/00 ,  B23B39/04 ,  B23B39/10 ,  B23Q11/10

Abstract: A machining device for producing at least one orifice in a workpiece made of composite material, the machining device including a tool holder and at least one drill bit mounted on the tool holder, the drill bit being configured to be driven in rotation about an axis of rotation. The machining device includes a cylindrical guide body coaxial with the axis of rotation, mounted on the tool holder, and surrounding the drill bit, the guide body being configured to bear on the workpiece during the production of the orifice and the drill bit projecting from the guide body.