Radially captured in situ balancing masses for aircraft powerplant

Abstract

An aircraft powerplant assembly includes a compressor section, a combustor section, a turbine section, a flowpath and a rotating structure. The flowpath extends through the compressor section, the combustor section and the turbine section. The rotating structure includes a balancing device and a bladed rotor disposed in the turbine section or the compressor section. The balancing device is configured to rotationally balance the rotating structure about a rotational axis of the rotating structure. The balancing device includes a mounting platform and a plurality of balancing masses. The mounting platform includes a plurality of mounting apertures. The balancing masses are arranged circumferentially about the axis. Each of the balancing masses includes a shank and a head. The shank of each of the balancing masses is threaded into a respective one of the mounting apertures. The head of each of the balancing masses is disposed radially inboard of the mounting platform.

Dependencies are inferred from the claim text.