Abstract: The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).

Abstract: The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).

Abstract: The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.

Abstract: A guide vane for a gas turbine engine, the guide vane including an airfoil made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers agglomerated in the form of a mat, the airfoil being provided at least on a leading edge with a reinforcing strip, the reinforcing strip being made from a single strip of unidirectional fabric or of textile, or by stacking a plurality of pre-impregnated plies of unidirectional fabric or of textile made of carbon fibers or of glass fibers, and at least one platform positioned at a radial end of the airfoil, the platform being made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers.

Abstract: A composite vane for a turbine engine, the vane having a pressure side face (12) and a suction side face (14) that define the aerodynamic profile of the vane, the vane (10) comprising: a metallic core (20) forming the pressure side face (12) or the suction side face (14) of the vane; and an organic matrix (30) associated with the metallic core (20).

Abstract: The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.