Method for manufacturing a blade for an aircraft turbine engine

A method for manufacturing a vane comprising a blade for an aircraft turbine engine, the method comprising the following steps:

• providing a fibrous preform of the blade, the fibrous preform comprising a leading edge, a trailing edge, and a pressure side face connected to a suction side face by the leading edge and the trailing edge,
• providing an elongate metal foil comprising at least one indexing recess,
• providing an injection mold comprising at least upper and lower parts configured to cooperate to delimit an internal volume and each defining a pattern of the vane, and at least one of these upper and lower parts comprising at least one projecting positioning element,
• arranging the fibrous preform in the injection mold,
• coating the leading edge of the fibrous preform with the metal foil, and inserting the projecting positioning element into the indexing recess so as to hold the metal foil in position on the leading edge, and
• injecting a resin into the injection mold in order to impregnate the fibrous preform and to attach the metal foil to the leading edge.