Abstract: An inner ring for supporting variable-pitch blades of an axial compressor stator of a turbomachine includes two or more ring sectors, assembled to form the inner ring, each ring sector including plural housings for receiving a pivot axis of one of the blades. At each junction plane between the ends of two successive ring sectors, an assembly pin and a cavity for receiving the assembly pin are engaged. The assembly pin is fixed on one end one of the two successive ring sectors and the cavity is formed at the end of the other of the two successive ring sectors. The cavity receives the assembly pin with a mounting clearance allowing a mounting by sliding fit, and the assembly pin is made of a material having a coefficient of thermal expansion greater than a coefficient of thermal expansion of a material constituting the successive ring sectors.

Abstract: An aircraft turbomachine rotor has a rotor disc extending transversely with respect to a longitudinal axis X, a plurality of blades, and a damping device. The damping device having: a support ring arranged transversely with respect to the longitudinal axis X and mounted on the outer periphery of the rotor disc, and has a plurality of damping members that are attached to the support ring and project upstream from the support ring, each damping member being configured to extend at least under a platform of a blade so as to exert a radially outward force to dampen the radial movement of the blade when the turbomachine is in operation.

Abstract: An aircraft turbomachine rotor comprising a rotor disc extending transversely with respect to a longitudinal axis X, a plurality of blades and a damping device comprising: a support ring configured to extend transversely with respect to the longitudinal axis X and configured to be mounted on the outer periphery of the rotor disc, and a plurality of damping members that are secured to the support ring and extend projecting upstream from the support ring, each damping member being configured to extend at least under a platform of a blade so as to exert a radially outward force so as to damp the radial movement of said blade when the turbomachine is in operation.