US 11,852,033 B2
Rotor blade for a turbomachine
Youssef Bouchia, Moissy-Cramayel (FR); and Laurent Pierre Tarnowski, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/760,018
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Feb. 4, 2021, PCT No. PCT/FR2021/050213
§ 371(c)(1), (2) Date Aug. 3, 2022,
PCT Pub. No. WO2021/156577, PCT Pub. Date Aug. 12, 2021.
Claims priority of application No. 2001221 (FR), filed on Feb. 7, 2020.
Prior Publication US 2023/0053734 A1, Feb. 23, 2023
Int. Cl. F01D 5/20 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/145 (2013.01) [F01D 5/20 (2013.01); F05D 2220/323 (2013.01); F05D 2240/307 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A rotor vane for a turbomachine, in particular of an aircraft, comprising a blade comprising a pressure face and a suction face extending from a leading edge to a trailing edge, the blade comprising an elongation axis extending substantially along the leading and trailing edges, the blade comprising a radially inner end for connection to a rotor and a radially outer free end,
wherein the blade further comprises at least one series of fins located on said free end, each of these fins comprising a pressure face located on the side of the suction face of the blade, and a suction face located on the side of the pressure face of the blade,
wherein ends of each of the fins are spaced from the suction face and pressure face of the blade.