The present disclosure is directed to a gas turbine engine assembly having a compressor 24 configured to increase pressure of incoming air, a combustion chamber 104, at least one turbine 106, 108 coupled to a generator 114, a torsional damper 116, and a controller 120. The combustion chamber 104 is configured to receive a pressurized air stream from the compressor 24. Further, fuel is injected into the pressurized air in the combustion chamber 104 and ignited so as to raise a temperature and energy level of the pressurized air. The turbine 106, 108 is operatively coupled to the combustion chamber 104 so as to receive combustion products that flow from the combustion chamber 104. The generator 114 is coupled to the turbine 106, 108 via a shaft 118. Thus, the torsional damper 116 is configured to dampen torsional oscillations of the generator 114. Moreover, the controller 120 is configured to provide additional damping control to the generator 114.