Fibrous texture for turbine engine blade made of composite material
The invention relates to a fibrous texture intended to form the fibrous reinforcement of a turbine engine blade made of composite material, the texture being in a single piece and having a three-dimensional weave between a plurality of first fiber warp yarns or strands extending in a radial direction and a plurality of first fiber weft yarns or strands extending in a chord direction, the texture comprising a blade root portion and a blade airfoil portion extending between the blade root portion and a free end of the fibrous texture. The blade airfoil portion has a reinforced area in the vicinity of the free end of the texture comprising weft yarns or strands made of second fibers different from the first fibers.
1. A blade for a turbine engine made of composite material comprising a fibrous reinforcement densified by a matrix, the fibrous reinforcement consisting of a fibrous texture, the texture being in a single piece and having a three-dimensional weave between a plurality of first fiber warp yarns or strands extending in a radial direction and a plurality of first fiber weft yarns or strands extending in a chord direction, the texture comprising a blade root portion and a blade airfoil portion extending between the blade root portion and a free end of the fibrous texture opposite the blade root,
wherein the blade airfoil portion has a reinforced area in the vicinity of the free end of the texture comprising weft yarns or strands made of second fiber different from the first fiber, the second fiber having an elongation at break greater than that of the first fiber, and in that a first ratio of second fiber in the reinforced area is greater than a second ratio of second fiber in the remainder of the rest of the blade airfoil portion.
2. The blade according to claim 1 , wherein the reinforced area extends from the free end of the fibrous texture over a length less than or equal to 40% of the total length of the texture measured in the radial direction.
3. The blade according to claim 1 , wherein, in the reinforced area, the second fiber weft yarns or strands are mostly present in a surface layer of the fibrous texture.
4. The blade according to claim 3 , wherein the texture has a face-corresponding to a suction face of the blade, and the layer extends from said face.
5. The blade according to claim 1 , wherein the first fibers are made of carbon and the second fibers are made of a material chosen from the following: glass, basalt, aramid or polyester.
6. The blade according to claim 1 , wherein the first ratio is between 10% and 70%.
7. The blade according to claim 1 , wherein the blade is a fan blade.
8. The fan blade according to claim 7 , further comprising a metallic leading-edge, said metallic leading edge covering ends of the second fiber weft yarns or strands of the reinforced area of the fibrous reinforcement.
9. An aeronautical turbine engine comprising a fan comprising a rotating disc and a plurality of blades according to claim 7 mounted on the rotating disc.