Axisymmetric part for an aviation turbine engine rotor

A link part for a turbine engine, the link part being mounted between a fan cone and a fan disk supporting fan blades, said link part comprising:

• an annular wall pierced by a plurality of orifices, each orifice for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface providing an aerodynamic extension between an outer surface of said fan cone and an outer surface of a fan blade platform,
• wherein said annular wall is made of a short-fiber composite material and is provided on an inner surface of said rim with a ring made of a long-fiber composite material that is different from the short-fiber composite material and is suitable for radially retaining said fan blade platform,
• wherein said outer surface providing the aerodynamic extension is covered in a fabric of composite material for withstanding lightning or erosion, and
• wherein the ring abuts the fan blade platform.