Method for manufacturing a composite material vane with an attached metal leading edge

A method for manufacturing a blade in composite material with added metal leading edge for gas turbine aeroengine, the method comprising:

• producing a batch of plurality of blade bodies in composite material;
• creating a digital model of a blade body from a blade in the batch of plurality of blade bodies;
• calculating a geometry of an inner wall of the leading edge intended to be bonded onto a foremost edge portion using the digital model of the blade body, the calculating including using a definition of a determined uniform thickness of adhesive or bonding material between the inner wall of the leading edge and a surface of the foremost edge;
• creating a digital model of a theoretical final blade comprising a leading edge;
• generating a digital model of the leading edge from the digital model of the blade body and the theoretical final blade model;
• manufacturing at least one leading edge via additive manufacturing from the generated leading edge digital model, and
• bonding each manufactured leading edge onto each blade body from the batch of plurality of blade bodies.