Turbomachine rotor blade for compressor of e.g. turboprop, has stop whose central portion includes thickness in direction perpendicular to end surface that is less than that of ends of stop

摘要

The blade (12) has a root (14) with a stop (44) formed in a protrusion on one of upstream and downstream end faces of the root, where a central portion of the stop includes thickness in a direction perpendicular to an end surface that is less than that of ends of the stop. The central portion of the stop is lightened by removal of a material, where the lightened or removed central portion of the stop has length in the direction substantially perpendicular to a longitudinal axis of the blade and parallel to one of the end faces.