FIELD: transport.
SUBSTANCE: invention relates to production of aircraft engineering, particularly, to helicopter anti-torque rotors. Rotorcraft rotor (10) enclosed in the cowl comprises the spinning assembly fitted in the channel to run about axis (AX1). Said spinning assembly (15) comprises multiple blades (20) each being secured at the boss (16). Note here that every blade (20) complies with the twist angle restricted by zero and 5 degrees incl. Every blade (20) comprises the first zone (21) and second sweepback zone (22) located over the blade span. The second zone comprises the second trailing edge (30" located downstream of the first trailing edge (30') of said first zone (21). Every first zone (21) with butt (24) engaged with the boss (16) by means of the fastening device (40) including the antifriction bearing (45) and conical laminar thrust (50).
EFFECT: higher strength and linearity in the rotor operation.
14 cl, 5 dwg
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