公开(公告)号：US20130202449A1

公开(公告)日：2013-08-08

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

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, in particular such as a turbojet, the link part being mounted between a fan cone and a fan disk supporting fan blades, the link part having an annular wall pierced by a plurality of orifices, each 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 being 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: 一种用于涡轮发动机的链接部件，特别是诸如涡轮喷气发动机的连杆部件，所述连杆部件安装在风扇锥体和支撑风扇叶片的风扇盘之间，所述连杆部件具有被多个孔刺穿的环形壁，每个孔口用于接收 紧固件构件并且由具有外表面的基本上垂直的边缘端接，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之间提供风扇的空气动力学延伸，所述环形壁由第一材料制成， 并且设置在边缘的内表面上，具有由与第一材料不同的并且适于径向保持风扇叶片平台的第二材料制成的环。

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：US20130111873A1

公开(公告)日：2013-05-09

申请号：US13718532

申请日：2012-12-18

Applicant: AIRCELLE ,  SNECMA

Inventor： Wouter BALK ,  François GALLET ,  Nicolas DEZEUSTRE ,  Oliver KERBLER

IPC: F02C3/08

CPC classification number: F02K3/06 ,  B64D33/02 ,  F01D21/045 ,  F05D2240/14 ,  F05D2300/433 ,  F05D2300/603 ,  Y02T50/672

Abstract: An aircraft turbojet engine fan casing in the form of a box section is provided by the present disclosure. The box section includes a radially interior wall of which is able to form an internal skin of a cold air flow duct of a nacelle in which said turbojet engine is intended to be mounted, and a radially exterior wall of which is able to form an external skin of said nacelle, the box forming a module forming an entire thickness of the nacelle, and placed between an upstream portion of the nacelle, forming the air intake, and a downstream casing portion, on which a cascade edge of a thrust reverser can be fixed.

Abstract translation: 本发明提供了一种箱体形式的飞机涡轮喷气发动机风扇壳体。 箱部分包括其径向内壁，其能够形成机舱的冷空气流动管道的内部皮肤，其中所述涡轮喷气发动机将被安装在其中，并且其径向外壁能够形成外部 所述机舱的壳体形成形成机舱整个厚度的模块，并且放置在机舱的上游部分，形成进气口和下游壳体部分之间，推力反向器的级联边缘可以在该下游壳体部分上 固定。

公开(公告)号：US20130108432A1

公开(公告)日：2013-05-02

申请号：US13718562

申请日：2012-12-18

Applicant: AIRCELLE ,  SNECMA

Inventor： Bertrand DESJOYEAUX ,  Nicolas DEZEUSTRE ,  Wouter BALK ,  François GALLET

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F01D5/282 ,  F01D5/34 ,  F01D9/04 ,  F01D25/24 ,  F02C7/04 ,  F02C7/20 ,  F02K3/06 ,  F05D2240/14 ,  F05D2250/51 ,  F05D2300/603 ,  Y02T50/672

Abstract: An airflow-straightening structure for an aircraft engine is provided that includes a hoop inside which there are arranged a plurality of flow-straightening vanes bearing a hub of a fan. Also includes is a clevis for connecting to a suspension strut, the clevis being fixed to said hoop. The structure has at least two elements chosen from the group of the hoop, the plurality of vanes, the hub and the clevis, which are formed in one piece, that is to say without any assembly operation. Additionally, at least one of the elements chosen from the group is at least partially formed of a composite material.

Abstract translation: 提供了一种用于飞行器发动机的气流矫直结构，其包括箍，其内布置有多个带有风扇毂的流动整流叶片。 还包括用于连接到悬架支柱的U形夹，U形夹固定到所述箍。 该结构具有至少两个元件，其选自环形组，多个叶片，轮毂和U形夹组，其形成为一体，也就是说没有任何组装操作。 另外，从组中选择的至少一个元素至少部分地由复合材料形成。

公开(公告)号：US20210317755A1

公开(公告)日：2021-10-14

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

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：US20150377282A1

公开(公告)日：2015-12-31

申请号：US14764871

申请日：2014-02-03

Applicant: SAFRAN

Inventor： Cedric THOMAS ,  Patrick DUNLEAVY ,  Wouter BALK

IPC: F16C3/02 ,  B29C70/52 ,  B29C53/56 ,  B29C70/16

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.

Abstract translation: 一种通过拉挤生产由复合材料制成的旋转运动传动轴的中空主体的方法，所述方法包括：浸渍加强件; 在拉挤拉杆周围布置增强织物以包裹拉挤成型卡盘，所述织物包括布置在与卡盘的纵向轴线正交的平面中的周向纤维; 然后将浸渍的增强物沉积在增强织物周围。

公开(公告)号：US20130258583A1

公开(公告)日：2013-10-03

申请号：US13851458

申请日：2013-03-27

Applicant: SAFRAN

Inventor： Wouter BALK ,  Robin Mandel

IPC: H05K5/03 ,  H05K5/02 ,  G06F1/20

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。