Active synchronizing ring
AssigneeRolls-Royce North American Technologies Inc.
InventorMichael P. Dougherty
Life of this patent
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Abstract
An improved system, apparatus and method for controlling vane angles in a gas turbine engine, and more specifically, for correcting vane angle error in a gas turbine engine. An active synchronization ring comprises a plurality of micro-actuators coupled to the synchronization ring to correct distortion in the synchronization ring. The micro-actuators apply a bending moment to the synchronization ring to cancel or compensate for synchronization ring distortion. The micro-actuators may be controlled open loop or closed loop. Strain sensors measure ring distortion and provide signals to the controller for closed loop control.
Claims21
A system for a gas turbine engine, comprising:
- a synchronization ring associated with individual vane positions;
- at least one sensor positioned along a circumference of the synchronization ring and configured to measure distortion of the synchronization ring;
- and
- at least one actuator positioned along the circumference of the synchronization ring and in communication with the at least one sensor, the at least one sensor being configured to communicate the measured distortion to the at least one actuator, and the at least one actuator being configured to reduce variance in the individual vane positions by countering the measured distortion from the at least one sensor by applying a bending moment relative to the circumference of the synchronization ring.
A device for a gas turbine engine, comprising:
- a synchronization ring including a plurality of sensors and a plurality of micro-actuators, the plurality of sensors being in communication with the plurality of micro-actuators, and the plurality of sensors being configured to measure distortion along a circumference of the synchronization ring and communicate the measured distortion to the plurality of micro-actuators, and
- wherein the plurality of micro-actuators is configured to create a bending moment relative to the circumference of the synchronization ring.
A device for a gas turbine engine, comprising:
- a synchronization ring including a circumference;
- a plurality of sensors along the circumference;
- a plurality of micro-actuators along the circumference;
- a shaft,
- wherein the plurality of sensors is in communication with the plurality of actuators, measures distortion of the synchronization ring, and communicates the measured distortion to the plurality of micro-actuators, and
- wherein the plurality of micro-actuators creates a bending moment in the synchronization ring.
Dependencies are inferred from the claim text.