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US 2023/0053734 A1Published application
Rotor blade for a turbomachine
AssigneeSafran Helicopter Engines
InventorsYoussef BOUCHIA, Laurent Pierre TARNOWSKI
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AssigneeSafran Helicopter Engines
InventorsYoussef BOUCHIA, Laurent Pierre TARNOWSKI
Estimating the term…
The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially firmer end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).
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, characterized in that it 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.
Dependencies are inferred from the claim text.