Patent ID: 8702377
Filing Date: 2014-04-22
Classification: F01D,F05D,Y10T

Abstract:
1. A gas turbine engine rotor tip clearance and shaft dynamics system, comprising: an engine case; a gas turbine engine disposed within the engine case, the gas turbine engine including a rotor; a rotor bearing assembly disposed within the engine case and rotationally mounting the gas turbine engine rotor therein; a plurality of vibration isolators mounted on the engine case and coupled to the rotor bearing assembly, each vibration isolator configured to provide linear and independently tunable stiffness and damping, each of the vibration isolators comprising a plurality of adjustment devices adjustably coupling the vibration isolator to the rotor bearing assembly; a plurality of actuators, each actuator coupled to at least one adjustment device in one of the vibration isolators and coupled to receive actuation control signals, each actuator responsive to the actuation control signals it receives to move the at least one adjustment device and thereby actively control gas turbine engine rotor position and dynamics; and an actuator control operable to selectively supply the actuation control signals to each actuator.