公开(公告)号：US20240293988A1

公开(公告)日：2024-09-05

申请号：US18571057

申请日：2022-06-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Maxime Mathieu MOUROT ,  Lucas Antoine Christophe LAUWICK ,  Julien TREBAOL

IPC: B29D99/00 ,  F01D5/14

CPC classification number: B29D99/0025 ,  F01D5/147 ,  F05D2220/36 ,  F05D2230/10 ,  F05D2230/60

Abstract: A method for manufacturing a blade made of a composite material for a turbine engine, in particular a turbine engine of an aircraft, wherein a reinforcing shield is attached to one edge of an airfoil, the shield having a generally elongated shape along an elongation axis of the airfoil. The shield includes at least one excess dimension so as to be able to adjust the moment weight of the blade along the axis according to the position of the shield on the edge of the axis, and the method includes a step for removing a surplus portion of the shield so s to balance the blade.