| 摘要 |
<p>A link part 26 for a turbine engine, eg a turbojet, the link part being mounted between a fan cone 24 and a fan disk 21 supporting fan blades, has an annular wall 28 pierced by a plurality of orifices 28A for receiving a fasteners 30 and is terminated by a substantially perpendicular rim 32. The rim 32 has an outer surface 32A providing an aerodynamic extension between the outer surfaces 24A, 22A of the fan cone and of a fan blade platform 22, respectively. The link part 26 is made of a first material that is composite and is provided on an inner surface (32B) of the rim 32 with a ring (34) made of a second material than is different from the first and that is suitable for radially retaining the fan blade platform 22. The first material may be thermosetting or thermoplastic composite, short-fibre sheet-moulding compound (SMC) or bulk-moulding compound (BMC). The second material may be titanium, an alloy based on titanium or aluminium, or a long-fibre composite material.</p> |
