Composite propeller vane or blade for aircraft integrating a conformation part

摘要

Composite propeller vane or blade 10 for an aircraft comprises a fiber reinforcement 200 having a three-dimensional weaving densified by a matrix. The fiber reinforcement 200 comprising in a single woven part a root portion 212 and an airfoil portion 211 extending along a longitudinal direction DL between the root portion and a vane tip portion 211d and along a transverse direction DT between a leading edge portion 211a and a trailing edge portion 211b. The airfoil portion 211 includes first and second extrados and intrados faces 211e, 211f. The fiber reinforcement includes a non-interlinking region 103 forming a housing 206 inside the fiber reinforcement and a conformation part 50 is present in the housing. The non-interlinking 103 extends over a non-interlinked area inside the airfoil portion 211 of the fiber reinforcement 200 comprised between the root portion 212 and the vane tip portion 211d in the longitudinal direction and between the leading edge portion 211a and the trailing edge portion 211b in the transverse direction, the non-interlinking 103 also opening outside the airfoil portion of the fiber reinforcement.