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：US20250115040A1

公开(公告)日：2025-04-10

申请号：US18903734

申请日：2024-10-01

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Pierre Antoine BOSSAN ,  Sophie ESSAYAN ,  Allison GLUGLA ,  Jordan KUSCH ,  Benjamin SAMSON

IPC: B32B37/12 ,  B29C65/00 ,  B29C65/48 ,  B29C65/50 ,  B29C65/52 ,  B29L31/08 ,  B32B7/06 ,  B32B7/12 ,  B32B15/08 ,  B32B27/20

Abstract: An adhesively bonded assembly of a first substrate on a second substrate by means of an adhesive joint integrating a support mesh, wherein the support mesh is present after curing over the entire adhesively bonded zone between the first and second substrates.

公开(公告)号：US20180196412A1

公开(公告)日：2018-07-12

申请号：US15840034

申请日：2017-12-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Clémence Virginie Charlotte BISOT ,  Alice Mathilde MARBOEUF ,  Benjamin SAMSON

IPC: G05B19/418

Abstract: The invention relates to a method of assembling parts chosen respectively from a plurality of first parts and a plurality of second parts. It comprises: for each first part and each second part of the plurality of first parts and the plurality of second parts the estimation of a defectiveness indicator for the assembly of the first part with the second part; for a batch of N assemblies is to be made, assignment (AFF) of N first parts from the plurality of first parts to N second parts from the plurality of second parts to form N pairs ({Ai, Bj}) of a first part and of a second part, said assignment being performed in such a way that said N pairs minimise a total defectiveness of the assembly. Application to the assembly of a blade and of a leading-edge reinforcement.

公开(公告)号：US20220266584A1

公开(公告)日：2022-08-25

申请号：US17618182

申请日：2020-06-18

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Pierre Antoine BOSSAN ,  Sophie ESSAYAN ,  Allison GLUGLA ,  Jordan KUSCH ,  Benjamin SAMSON

IPC: B32B37/12 ,  B32B7/12 ,  B32B7/06 ,  B32B15/08 ,  B32B27/20 ,  B29C65/48 ,  B29C65/50 ,  B29C65/52 ,  B29C65/00

Abstract: A method of adhesively bonding a first substrate on a second substrate in an adhesive bonding zone by an adhesive joint integrating a support mesh, wherein surplus adhesive joint is folded over onto one or the other of the first or second substrates so that the support mesh is present over the entire adhesively bonded zone after curing.