公开(公告)号：US11629644B2

公开(公告)日：2023-04-18

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 ,  B29C33/00 ,  B29C45/00 ,  B29C45/37 ,  B29K105/04 ,  B29L31/60

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：US09204566B2

公开(公告)日：2015-12-01

申请号：US13851458

申请日：2013-03-27

Applicant: SAFRAN

Inventor： Wouter Balk ,  Robin Mandel

IPC: H05K7/20 ,  H05K5/03 ,  H05K5/00 ,  H05K5/02 ,  G06K1/20 ,  H01L23/473

CPC classification number: H05K5/03 ,  G06F1/20 ,  G06K1/20 ,  H05K5/0073 ,  H05K5/0213 ,  H05K5/0234 ,  H05K7/20127

Abstract: A device for protecting a computer of an aircraft turbine engine, the device comprising a box containing the computer and a cover covering the box, the box being supported by tabs forming integral portions of the box and maintaining a flow of air between the bottom of the box and a portion of the casing of the engine on which they are to come into secure contact via resilient studs, the box being made of a composite material.

Abstract translation: 一种用于保护飞机涡轮发动机的计算机的装置，该装置包括容纳计算机的盒和覆盖盒的盖，该盒由形成盒的整体部分的突出部支撑，并且保持在该底部之间的空气流 箱体和发动机壳体的一部分，它们将通过弹性螺柱与其紧密接触，该箱体由复合材料制成。

公开(公告)号：US20150021455A1

公开(公告)日：2015-01-22

申请号：US14377644

申请日：2013-02-05

Applicant: SAFRAN ,  SNECMA

Inventor： Robin Mandel ,  Wouter Balk ,  Nicolas Christian Raymond Leblond ,  Jean-Yves Picart

IPC: F02C7/32

CPC classification number: F02C7/32 ,  F01D25/28 ,  F02C7/25 ,  F05D2300/603

Abstract: A turbine engine support part including a main structure made of composite material and a reinforcing secondary structure made of metal and integrated in the main structure, the secondary structure presenting a geometrical shape and dimensions configured to impart mechanical strength to the support part in event of the main structure being destroyed.

Abstract translation: 一种涡轮发动机支撑部件，包括由复合材料制成的主结构和由金属制成并且集成在主结构中的加强二次结构，所述二次结构呈现几何形状和尺寸，其被配置为在所述主结构中发生机械强度以赋予所述支撑部分 主体被破坏。

公开(公告)号：US09850939B2

公开(公告)日：2017-12-26

申请号：US14764871

申请日：2014-02-03

Applicant: SAFRAN

Inventor： Cedric Thomas ,  Patrick Dunleavy ,  Wouter Balk

IPC: B65H81/00 ,  F16C3/02 ,  B29C70/52 ,  B29C70/22 ,  B29C53/56 ,  B29C70/16 ,  B29C53/58 ,  B29K63/00 ,  B29K105/08 ,  B29L31/00

CPC classification number: F16C3/026 ,  B29C53/56 ,  B29C53/58 ,  B29C70/16 ,  B29C70/222 ,  B29C70/52 ,  B29C70/521 ,  B29K2063/00 ,  B29K2105/0809 ,  B29L2031/75

Abstract: A method for producing by pultrusion a hollow main body of a rotary movement transmission shaft made of a composite material, the method including: impregnating a reinforcement; arranging a reinforcing fabric around a pultrusion chuck to wrap the pultrusion chuck, the fabric including circumferential fibers arranged in planes orthogonal to a longitudinal axis of the chuck; and then depositing the impregnated reinforcement around the reinforcing fabric.

公开(公告)号：US11649738B2

公开(公告)日：2023-05-16

申请号：US17273898

申请日：2019-09-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Antonin Etienne Diego Tessiereau ,  Cyrille François Antoine Mathias ,  Wouter Balk

IPC: F01D25/28 ,  F01D25/00 ,  F01D25/24 ,  F01D9/02

CPC classification number: F01D25/28 ,  F01D9/02 ,  F01D25/005 ,  F01D25/24 ,  F05D2240/14 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2260/31 ,  F05D2260/606 ,  F05D2300/603

Abstract: The invention relates to an assembly for a turbomachine with a longitudinal axis comprising a first annular wall (24), panels (38) being arranged around the longitudinal axis (A) and extending radially opposite said first annular wall (24) so as to form a flow surface for a flow of air, each panel (38) being secured to the first annular wall (24) by at least one fixing member (72) passing through an orifice in the panel (38) and secured to the first annular wall (24) by means of a sleeve and a stud forming a spacer.

公开(公告)号：US09284842B2

公开(公告)日：2016-03-15

申请号：US13761744

申请日：2013-02-07

Applicant: SAFRAN ,  SNECMA

Inventor： Jean-Pierre Francois Lombard ,  Wouter Balk ,  Sebastien Pautard ,  Benjamin Samson ,  Benjamin Kiener-Calvet ,  Frederic Rogues

IPC: F01D5/02 ,  F02K3/06 ,  F01D5/30 ,  F04D29/32 ,  B64C11/14 ,  F04D29/64 ,  F01D5/32

CPC classification number: F01D5/02 ,  B64C11/14 ,  F01D5/025 ,  F01D5/3007 ,  F01D5/3015 ,  F01D5/326 ,  F02K3/06 ,  F04D29/023 ,  F04D29/321 ,  F04D29/325 ,  F04D29/326 ,  F04D29/329 ,  F04D29/644 ,  F04D29/646 ,  F05D2260/30 ,  F05D2300/603

Abstract: A link part for a turbine engine which mounted between a fan cone and a fan disk supporting fan blades is provided. The link part includes an annular wall pierced by a plurality of orifices, each orifice for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform. The annular wall is made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform.

Abstract translation: 提供一种用于涡轮发动机的连接部件，其安装在风扇锥体和支撑风扇叶片的风扇盘之间。 连接部分包括由多个孔刺穿的环形壁，每个孔用于接纳紧固件构件，并且由基本上垂直的边缘端接，所述边缘具有外部表面，所述外表面在风扇锥体的外表面和 风扇叶片平台的外表面。 环形壁由复合的第一材料制成，并且设置在边缘的内表面上，具有由与第一材料不同的适于径向保持风扇叶片平台的第二材料制成的环。