公开(公告)号：US10240463B2

公开(公告)日：2019-03-26

申请号：US15070585

申请日：2016-03-15

Applicant: SNECMA

Inventor： Gilles Pierre-Marie Notarianni ,  Matthieu Arnaud Gimat ,  Jérémy Guivarc'h ,  Thibault Ruf

IPC: F01D5/14 ,  B29C70/48 ,  B29C70/86 ,  B29D99/00 ,  B64C11/20 ,  F01D5/28 ,  D05B23/00 ,  B29L31/08 ,  B29K705/00

Abstract: A blade made of organic matrix composite material for a gas turbine aeroengine, includes an airfoil extending transversely between a leading edge and a trailing edge; and a metal strip positioned on the leading edge of the airfoil, the metal strip having two flanges extending on either side of the leading edge over portions of the side faces of the airfoil forming a pressure side face and a suction side face so that the strip fits closely to the profile of the leading edge, the metal strip being fastened to the leading edge of the airfoil by at least one stitching thread; wherein the stitching thread has at least one external thread segment extending substantially transversely between a hole formed through a flange of the strip and a passage formed in a portion of the airfoil that has at least one face that is not covered by the metal strip.