Rotor blade damping structures

A turbomachine, comprising:

• a compressor section;
• a combustor section;
• a turbine section;
• a rotor disk provided in one of the compressor section or the turbine section, a first rotor blade and a second rotor blade mounted on the rotor disk adjacent to one another, the first rotor blade and second rotor blade each comprising:
• a platform;
• and
• an airfoil extending radially outward from a root coupled to the platform to a tip, the airfoil including a pressure side surface, a suction side surface, and a part-span shroud extending from the airfoil and disposed between the root and the tip, the part-span shroud having a pressure side portion extending from the pressure side surface and a suction side portion extending from the suction side surface, wherein the pressure side portion of the part-span shroud of the first rotor blade and the suction side portion of the part-span shroud of the second rotor blade form an interface joint with one another;
• and
• a first pin damper and a second pin damper each positioned within and extending between the part span shroud of the first rotor blade and the part span shroud of the second rotor blade at the interface joint, wherein the first pin damper and the second pin damper are movable relative to the part span shroud of both the first rotor blade and the second rotor blade.