ASSEMBLIES FOR AN AIRCRAFT POWERPLANT AND METHOD FOR BALANCING A ROTATING STRUCTURE OF A GAS TURBINE ENGINE

An aircraft powerplant (20) assembly includes a compressor section (36), a combustor section (37), a turbine section (38), a flowpath and a rotating structure (70). The flowpath extends through the compressor section (36), the combustor section (37) and the turbine section (38). The rotating structure (70) includes a balancing device (76) and a bladed rotor disposed in the turbine section (38) or the compressor section (36). The balancing device (76) is configured to rotationally balance the rotating structure (70) about a rotational axis (72) of the rotating structure (70). The balancing device (76) includes a mounting platform (108) and a plurality of balancing masses (88). The mounting platform (108) includes a plurality of mounting apertures (120). The balancing masses (88) are arranged circumferentially about the axis (72). Each of the balancing masses (88) includes a shank (130) and a head (128). The shank (130) of each of the balancing masses (88) is threaded into a respective one of the mounting apertures (120). The head (128) of each of the balancing masses (88) is disposed radially inboard of the mounting platform (108).