Patent ID: 9482102
Filing Date: 2016-11-01
CPC Classification: B23K,B29C,B29L,F01D,F04D,F05D,Y10T

Claim Text:
1. A method for producing a metal reinforcement for mounting on a leading edge or a trailing edge of a composite blade for a turbine engine, a fan blade of an airplane turboprop or turbojet, the metal reinforcement including a solid portion extended by first and second lips which are attached to pressure and suction side surfaces of the blade, the method comprising: providing first and second sheets of the metal reinforcement, each of the sheets including a first portion corresponding to the solid portion of the metal reinforcement and a second portion corresponding to a lip of the metal reinforcement, the first portion including a junction surface; providing at least one recess in each junction surface of the first and second sheets of the metal reinforcement; inserting a bundle of reinforcing fibers surrounded by a sheath of elongate shape at least in part in the recess; and assembling together the first and second sheets such that the junction surfaces of the first and second sheets abut each other; and diffusion bonding the first and second sheets to form the metal reinforcement.