Abstract: 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).

Abstract: 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).

Abstract: A wheel blade for a turbomachine compressor. The blade comprises a body extending between the root of the blade in the direction of the height of the blade. The body extends from a leading-edge to a trailing edge in a direction of the camber line of the blade. The blade comprises a winglet located in the extension of the body in the direction of the height. The winglet is located at the tip of the blade and at the leading edge of the blade. The body has a curvature oriented in a first direction of rotation with respect to the direction of the camber line, the winglet having a curvature in a second direction of rotation counter to the first direction of rotation.

Abstract: A wheel blade for a turbomachine compressor. The blade comprises a body extending between the root of the blade in the direction of the height of the blade. The body extends from a leading-edge to a trailing edge in a direction of the camber line of the blade. The blade comprises a winglet located in the extension of the body in the direction of the height. The winglet is located at the tip of the blade and at the leading edge of the blade. The body has a curvature oriented in a first direction of rotation with respect to the direction of the camber line, the winglet having a curvature in a second direction of rotation counter to the first direction of rotation.