FIELD: machine engineering.
SUBSTANCE: turbomachine rotor blade (112) comprising a root (113) and an tip (114) spaced by height (h) of blade having at least one intermediate segment (112a) between blade the root (113) and the tip (114) which has back sweep at least 50% of the blade height (h), and an end segment (112b) with a forward sweep between the intermediate segment (112a) and the blade tip (114), wherein the end segment (112b) also has angle of line inclination passing through centres of gravity (CG) of the blade successive profiles relative to the radial axis (Y) of the blade in the rotor rotation (R) direction.
EFFECT: invention further reduces the risk of dynamic self-engaging of the rotor blade comprising the end segment with direct sweep between the blade tip and the intermediate segment which has reverse sweep along the half of the blade height.
11 cl, 14 dwg
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