Semi-autonomous rapid response active clearance control system

1. A semi-autonomous rapid response active clearance control system for a gas turbine engine, the active clearance control system comprising:

an outer case;

a carrier for a blade outer airseal positioned radially inward of the outer case;

a blade outer airseal positioned radially inward of and mounted to the carrier;

at least one electromechanical actuator attached to the outer case and selectively operable to move the carrier; and

a sensing system comprising:

a maneuver sensor housed within the actuator and configured to output a first signal representing a change in at least one of a velocity and a rotation;

a position sensor mounted proximate the blade outer airseal and configured to output a second signal; and

a control means in communication with the maneuver sensor and the position sensor.

2. The system of claim 1 , wherein the maneuver sensor is an accelerometer and the first signal represents a change in velocity.

3. The system of claim 1 , wherein the maneuver sensor is a gyroscope and the first signal represents a change in rotation.

4. The system of claim 1 , wherein the position sensor senses a clearance between the blade outer airseal and a rotor blade tip.

5. The system of claim 4 , wherein the position sensor is a microwave sensor.

6. The system of claim 5 , wherein the position sensor is mounted radially outward of the blade outer airseal.

7. The system of claim 1 , wherein the control means comprises a controller for receiving the first signal and the second signal.

8. The system of claim 7 , wherein the controller is collocated with the at least one electromechanical actuator.

9. The system of claim 7 , wherein the controller is configured to signal the at least one electromechanical actuator to actuate a lever in response to at least one of the first signal or the second signal.

10. The system of claim 9 , wherein a first end of the lever is in operational contact with the at least one electromechanical actuator, and wherein a second end of the lever is in operational contact with the carrier.

11. The system of claim 1 , wherein the at least one electromechanical actuator comprises a plurality of electromechanical actuators.

12. A turbine section of a gas turbine engine comprising:

a first turbine stage comprising a plurality of blades rotatable about an engine axis;

each of the plurality of blades comprising a blade body and a tip at a radially outermost extent of the blade body; and

the active clearance control system of claim 1 ;

wherein the active clearance control system is configured to maintain a predetermined clearance between a radially inner side of the blade outer airseal and the tip of each of the plurality of blades.

13. A method of maintaining a predetermined clearance between an airfoil tip and a blade outer airseal within a gas turbine engine, the method comprising:

sensing a plurality of parameters using a closed-loop sensing system independently operable of a full authority digital electronic control of the gas turbine engine, the closed-loop sensing system comprising:

a maneuver sensor configured to sense a first parameter;

a position sensor configured to sense a second parameter; and

actuating, using an electromechanical actuator, a lever to adjust a radial position of the blade outer airseal based on the sensed first parameter and the sensed second parameter;

wherein the first parameter is a change in velocity or a change in rotation, and the second parameter is a clearance between the blade outer airseal and the airfoil tip.

14. The method of claim 13 , wherein the maneuver sensor is housed within the electromechanical actuator.

15. The method of claim 13 , wherein the maneuver sensor is an accelerometer or a gyroscope.

16. The method of claim 13 , wherein the position sensor is a microwave sensor.

17. The method of claim 13 and further comprising:

receiving, using a control means, a first output signal representative of the first parameter; and

receiving, using the control means, a second output signal representative of the second parameter.

18. The method of claim 17 and further comprising: signaling, using the control means, actuation of the electromechanical actuator based on at least one of the first output signal or the second output signal.

19. The method of claim 17 , wherein data representing the predetermined clearance is stored within the control means.

20. The method of claim 17 , wherein the control means is collocated with the electromechanical actuator.