Method for manufacturing composite material completed blade of turbojet of aircraft, involves manufacturing outline of termination element forming leading edge, and carrying out profile of leading edge on assembly of material and outline

摘要

The method involves manufacturing an outline (204) of a termination element (202) forming a leading edge. A composite material blade (201) and the outline of the termination element are assembled. A profile (208) of the leading edge is carried out on an assembly of a composite material and the outline of the termination element. A part with extra peripheral thickness (205) is produced with respect to the profile of the leading edge during manufacturing the outline, where the thickness lies between 1 mm and 5 mm. The leading edge of the termination element is made of titanium.