Abstract: A method for producing a blade includes providing a fibrous preform; providing a metal foil of elongate shape and including at least one indexing recess; and providing an injection mold having at least an upper part and a lower part. At least one of the upper part and the lower part includes at least one positioning projection. The method further includes the steps of arranging the fibrous preform in the injection mold; coating the leading edge of the fibrous preform with the metal foil, and inserting the positioning projection into the indexing recess so as to hold the metal foil in position on the leading edge. The method also further includes injecting a resin into the injection mold.

Abstract: A method for manufacturing a blade of a fan for an aircraft turbomachine extending around a longitudinal axis, the blade including an aerofoil made of a composite material having a leading edge and a trailing edge connected by a pressure side and a suction side, the aerofoil extending between a base and a free end, the method including each of the following steps: —pairing and bonding a metal shield to the leading edge, —obtaining a first measurement of a radial moment weight of the blade before or after the metal shield has been bonded to the leading edge and determining a machining kerf, —machining the free end and/or the trailing edge along the machining kerf so as to adjust the mass and radial moment weight of the blade, —obtaining a second measurement of the radial moment weight of the blade.

Abstract: A fibrous preform of a turbomachine vane or blade includes two fibrous portions formed by three-dimensional weaving and forming an aerodynamic profile of the vane or blade and defining therebetween an interior volume, wherein each fibrous portion has at least one fibrous vibration damping stiffener including one or several unidirectional layers of yarns and present in the interior volume, and wherein the at least one fibrous stiffener is present on a non-interlinked area on which the unidirectional layer(s) of yarns are separated from the corresponding fibrous portion, and wherein the yarns of this or these unidirectional layers are woven with the corresponding fibrous portion outside the non-interlinked area, or wherein the at least one fibrous stiffener is added onto each fibrous portion.

Abstract: A method for manufacturing a blade made of a composite material for a turbine engine, in particular a turbine engine of an aircraft, wherein a reinforcing shield is attached to one edge of an airfoil, the shield having a generally elongated shape along an elongation axis of the airfoil. The shield includes at least one excess dimension so as to be able to adjust the moment weight of the blade along the axis according to the position of the shield on the edge of the axis, and the method includes a step for removing a surplus portion of the shield so s to balance the blade.

Abstract: A method for manufacturing a blade of a fan for an aircraft turbomachine extending around a longitudinal axis, the blade including an aerofoil made of a composite material having a leading edge and a trailing edge connected by a pressure side and a suction side, the aerofoil extending between a base and a free end, the method including each of the following steps:—pairing and bonding a metal shield to the leading edge,—obtaining a first measurement of a radial moment weight of the blade before or after the metal shield has been bonded to the leading edge and determining a machining kerf,—machining the free end and/or the trailing edge along the machining kerf so as to adjust the mass and radial moment weight of the blade,—obtaining a second measurement of the radial moment weight of the blade.

Abstract: A fibrous preform of a turbomachine vane or blade includes two fibrous portions formed by three-dimensional weaving and forming an aerodynamic profile of the vane or blade and defining therebetween an interior volume, wherein each fibrous portion has at least one fibrous vibration damping stiffener including one or several unidirectional layers of yarns and present in the interior volume, and wherein the at least one fibrous stiffener is present on a non-interlinked area on which the unidirectional layer(s) of yarns are separated from the corresponding fibrous portion, and wherein the yarns of this or these unidirectional layers are woven with the corresponding fibrous portion outside the non-interlinked area, or wherein the at least one fibrous stiffener is added onto each fibrous portion.

Abstract: A method for manufacturing hollow composite material turbomachine part, includes producing a fibrous blank in one piece by three-dimensional weaving of yarns, the blank including at least one de-bonded zone forming an internal cavity, inserting a shaping part into the internal cavity of the fibrous blank in order to obtain a preform, densification of the preform by a matrix in order to obtain a structure having a fibrous reinforcement consisting of the preform densified by the matrix, wherein the shaping part is flexible and wherein the shaping part is mechanically withdrawn from the structure after the densification.