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：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。