The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement (20).