Damping device

An assembly method, comprising:

• positioning a damping device between a first rotor module and a second rotor module so that a first radial external surface of the damping device is supported with friction against the first rotor module and a second radial external surface of the damping device is supported with friction against the second rotor module, the first rotor module comprising disk centered on a turbomachine longitudinal axis and a first blade mounted on an external periphery of the disk, the first blade thus extending from the external periphery of the disk, the first blade further comprising an airfoil, a platform, a support and a root, the root being embedded in a housing of the disk, the first blade having a first length, the first radial external surface being supported with friction on a radially internal surface of the platform, the second rotor module being connected to the first rotor module and comprising a second blade and a ferrule, the ferrule comprising a circumferential extension extending toward the platform of the first blade, the second blade having a second length, the second length being smaller than the first length, the second radial external surface being supported with friction on the ferrule, the damping device extending with at least one component along the turbomachine longitudinal axis, the damping device being annular while extending circumferentially around the turbomachine longitudinal axis;
• and
• preloading the damping device against the first rotor module and the second rotor module, so as to couple the first rotor module with the second rotor module in order to damp vibrational movements of the first rotor module relative to the second rotor module during operation.