Method for producing a vane made from composite material

A method for producing a vane made from composite material for an aircraft turbomachine, the vane comprising a blade having a pressure side and a suction side interconnected by a leading edge and a trailing edge, the method comprising the following steps:

• (a) successively stacking several fibre layers to form a fibrous blank,
• (b) shaping said fibrous blank to obtain a fibrous preform of the blade, said fibrous preform comprising a pressure side skin and a suction side skin joined together and configured to form, respectively, the pressure side and the suction side of the blade, and
• (d) densifying said fibrous preform with a resin to form the vane made from composite material,
• wherein the fibrous blank comprises first and second portions continuously joined together in step (a),
• in that step (b) comprises folding the fibrous blank along a line extending between said first and second portions so as to form, on either side of the folding line, said pressure side and suction side skins, and in that the leading edge, or alternatively the trailing edge, of the blade is located at the level of and along this folding line, and edges of the pressure side and suction side skins, opposite this folding line, being joined together to form the leading edge, or alternatively the trailing edge, of the blade;
• in that the fibrous blank and/or the fibrous preform are formed on a surface of a support which is planar, U-curved or V-curved, said surface of the support further comprises a U- or V-shaped projecting portion configured to define said folding line;
• and in that the method comprises, in step (a), a step (i) of preforming at least part of the fibrous blank formed on said U- or V-shaped projecting portion of the support.