A blade intended to be mounted on a turbomachine rotor with an axis, the blade including a root configured to be mounted in a groove that opens to the outer periphery of a disk of the turbomachine rotor; an airfoil extending the root, in a radial direction with respect to the axis, and having an aerodynamic profile; a radially inner platform separating the airfoil from the root; a heel which extends as a continuation of the airfoil at a free radial end of the blade, at the end of the airfoil radially opposite the root, the heel including a radially outer platform, wherein the heel includes means for locking the radially outer platform with respect to another circumferentially adjacent radially outer platform.