FIELD: engines and pumps.
SUBSTANCE: aircraft turbojet fan (1) comprises a plurality of fan blades (10). Each blade includes an aerodynamic vane (15), a blade root (12) held in one of the recesses (8) of the disc, and a support (13) inserted between the vane and the root. Support includes a rear portion having a first surface (13a) located on the pressure side (20) of the vane and a second surface (13b) located on the suction side (22) of the vane. Fan disc (2) comprises, between the recesses (8), attaching flanges (26) protruding radially outwards such that the first surface and the second surface (13a, 13b) are located respectively opposite the two attaching flanges (26, 26). Fan comprises a wear-resistant part (40) mounted on the blade so as to form a protective cover (32a, 32b) on each of the first and second surfaces (13a, 13b) of the support to prevent contact between each surface (13a, 13b) and the attaching flange (26, 26) located opposite it.
EFFECT: longer service life of the blade is achieved.
9 cl, 10 dwg
