Method for manufacturing a turbine engine vane made of a composite material, resulting vane and turbine engine including same

A method of fabricating a turbine engine blade, the blade being made of composite material comprising fiber reinforcement densified by a matrix and comprising an airfoil, a first platform situated at one longitudinal end of the airfoil and having an inside face defining a flow passage and an outside face opposite from the inside face, and at least one functional element projecting from the outside face of the first platform and connecting with said outside face in a direction that is substantially circumferential, the method comprising:

• making a single-piece fiber blank by multilayer weaving;
• shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for the blade airfoil and a second portion forming a preform for the first platform and a preform for the at least one functional element;
• and
• densifying the fiber preform with a matrix in order to obtain a composite material blade having fiber reinforcement formed by the preform and densified by the matrix and forming a single piece incorporating the airfoil, the first platform, and the at least one functional element;
• in which method the second portion of the preform comprises a set of yarn layers interlinked by weaving with at least one non-interlinked zone being arranged therein enabling the preform for the at least one functional element to be deployed relative to the preform for the first platform, and wherein the fiber blank portion corresponding to the second preform portion includes one or more yarn layers taken from the portion of the fiber blank corresponding to the airfoil preform at one or more locations positioned in the longitudinal direction, the airfoil preform being of varying thickness in the longitudinal direction.