Patent ID: 8573936

Claim:
A blade for an aircraft turbomachine receiving part, comprising: a root; and an airfoil part prolonging said root, said airfoil part including an aerodynamic shell surrounding a hollow structural core, wherein said blade further includes a bowl with a head at a first end thereof and a stem extending from said bowl head, said bowl head being located in said shell and said bowl stem being located outside said shell, said bowl stem presenting a junction with a reduced cross-section connecting said airfoil part to said root, wherein said hollow structural core extends along a length direction of said airfoil part and is located in external radial continuity with said bowl head such that a first end of said hollow structural core faces said bowl head, wherein a sleeve surrounds said first end of said bowl and said first end of said hollow structural core, and wherein said airfoil part includes a mechanical fuse provided at an interface between said bowl head and said hollow structural core, and the mechanical fuse is located at a distance from a bottom of the blade along the length direction of the airfoil part, between 0.25 and 0.5 times the length of said airfoil part along the length direction.