CPC F01D 5/288 (2013.01) [F01D 5/225 (2013.01); F05D 2220/323 (2013.01); F05D 2240/24 (2013.01)] | 8 Claims |
1. A rotor vane for an aircraft turbomachine, the rotor vane having
an axis of rotation and a stacking axis and comprising
a blade extending between an internal platform and an external platform bearing at least one projecting lip,
the blade comprising a pressure side and a suction side and the external platform comprising a pressure side lateral edge and a suction side lateral edge located on the pressure side and the suction side respectively, and each of the pressure side lateral edge and the suction side lateral edge configured to cooperate in a form-fitting manner with complementary lateral edges of adjacent vanes,
each of the pressure side lateral edge and the suction side lateral edge comprising a wear-resistant covering,
wherein the wear-resistant covering of the pressure side lateral edge extends over one first wall of a rectilinear first ridge, and over one second wall of a second ridge extending at least partially in the at least one projecting lip, the wall of the second ridge being inclined relative to the rectilinear first ridge in a direction parallel to a transverse axis of elongation of the at least one projecting lip, and the wall of the second ridge extending between 20 to a maximum of 50% of a height of the at least one projecting lip in which the second ridge extends, measured along the stacking axis.
|