System for attaching a turbomachine blade

A system for fixing a blade for a turbomachine, wherein it comprises:

• a blade for a turbomachine made monolithically of composite material from a blade preform made of woven composite material obtained by three-dimensional weaving, the blade preform having been shaped in a mold and embedded in a matrix, the blade preform having a general shape which is elongated in a first direction Y, representing the direction of a height of the blade, and which extends in two other perpendicular directions including a second axial direction Z representing the direction of a chord of the blade and a third transverse direction X representing the direction of a thickness of the blade, the blade preform comprising, aligned in the first direction Y, a lower area Z1 able to form a blade root and an upper area able to form a blade airfoil including a blade tip, the lower area being woven and shaped so as to comprise two skins spaced apart from each other in the transverse direction X, thus providing between the two skins a free space which forms a non-interlinking in the woven material, each skin being able to form a portion of the blade root,
• the blade including, at a level of the blade root, two portions of the blade root spaced apart from each other in the transverse direction X so as to provide therebetween a cavity which extends downwards in the direction Y of the height of the blade, from a cavity bottom to a cavity opening on an outside, located at the level of a lower end of the blade root,
• at least one attachment element of the blade which is partially engaged inside the cavity, an engaged part of said at least one attachment element having a shape, taken in a plane defined by the two directions X and Y, which extends towards the bottom of the cavity while flaring out in the transverse direction X, the two spaced apart portions of the blade root which are in contact with the flared shape of said at least one attachment element having corresponding flared shapes.