Method and apparatus for active clearance control for high pressure compressors using fan/booster exhaust air

1. A clearance control system for a turbomachine, the turbomachine including a rotatable member defining an axis of rotation, an inner annular casing extending directly over at least a portion of the rotatable member along a circumferential direction to define a clearance therebetween, the inner annular casing including a radially outer surface, the turbomachine further including an outer annular casing extending over at least a portion of the inner annular casing, the inner annular casing and the outer annular casing defining at least one cavity therebetween, the clearance control system comprising:

a manifold system comprising a plurality of supply tubes disposed within the at least one cavity, the plurality of supply tubes extending circumferentially about the inner annular casing; and

an impingement system disposed within the at least one cavity, the impingement system extending circumferentially about the inner annular casing, the plurality of supply tubes configured to channel a flow of a cooling fluid to the impingement system, the impingement system configured to channel the flow of the cooling fluid directly to the radially outer surface of the inner annular casing, wherein the at least one cavity is coupled in flow communication with the turbomachine.

2. The clearance control system of claim 1 , wherein the cooling fluid comprises air.

3. The clearance control system of claim 1 , wherein the manifold system comprises an air valve.

4. The clearance control system of claim 3 , further comprising a controller configured to control a position of the air valve.

5. The clearance control system of claim 1 , wherein the impingement system comprises a plurality of plenums disposed on the radially outer surface of the inner annular casing.

6. A method of controlling a clearance between a plurality of compressor blades and an inner annular casing, the method comprising:

defining at least one cavity between the inner annular casing and an outer annular casing;

channeling a flow of a cooling fluid from a cooling fluid source to a manifold system including a plurality of supply tubes disposed within the at least one cavity; and

channeling the flow of the cooling fluid directly from the manifold system to a radially outer surface of the inner annular casing via an impingement system disposed within the at least one cavity and positioned on the radially outer surface of the inner annular casing.

7. The method of claim 6 , wherein channeling the flow of the cooling fluid from the cooling fluid source to manifold system comprises channeling air from an air source to manifold system.

8. The method of claim 6 , wherein defining the at least one cavity between the inner annular casing and the annular outer casing comprises defining the at least one cavity between the inner annular casing and the annular outer casing in flow communication with a high pressure compressor.

9. The method of claim 6 , wherein defining the at least one cavity between the inner annular casing and the annular outer casing comprises defining the at least one cavity between the inner annular casing and the annular outer casing isolated from a high pressure compressor.

10. The method of claim 6 , wherein channeling the flow of the cooling fluid from the cooling fluid source to the manifold system including the plurality of supply tubes disposed within the the at least one cavity comprises channeling the flow of the cooling fluid from the cooling fluid source to an air valve disposed within the manifold system.

11. A turbomachine comprising:

a compressor comprising a rotatable member defining an axis of rotation, the compressor comprising:

an inner annular casing comprising a radially outer surface extending directly over at least a portion of the rotatable member along a circumferential direction to define a clearance therebetween; and

an outer annular casing extending over at least a portion of the inner annular casing, the inner annular casing and the outer annular casing defining at least one cavity therebetween; and

a clearance control system comprising:

a manifold system comprising a plurality of supply tubes disposed within the at least one cavity, the plurality of supply tubes extending circumferentially about the inner annular casing; and

an impingement system disposed within the at least one cavity, the impingement system extending circumferentially about the inner annular casing, the plurality of supply tubes configured to channel a flow of a cooling fluid to the impingement system, the impingement system is configured to channel the flow of the cooling fluid directly to the radially outer surface of the inner annular casing.

12. The turbomachine of claim 11 , wherein the cooling fluid comprises air.

13. The turbomachine of claim 11 , wherein the impingement system comprises a plurality of plenums disposed on the radially outer surface of the inner annular casing.

14. The turbomachine of claim 11 further comprising a plurality of walls disposed within the at least one cavity, wherein the plurality of walls separates the at least one cavity into a first region and a second region, the first region coupled in flow communication with the turbomachine, the plurality of walls is configured to isolate the second region from the first region, the clearance control system disposed within the second region.

15. The turbomachine of claim 14 , wherein the plurality of walls comprises a thermal insulating material.

16. The turbomachine of claim 11 , wherein the manifold system comprises an air valve.

17. The turbomachine of claim 16 further comprising a controller configured to control a position of the air valve.

18. A clearance control system for a turbomachine, the turbomachine including a rotatable member defining an axis of rotation, an inner annular casing extending directly over at least a portion of the rotatable member along a circumferential direction to define a clearance therebetween, the inner annular casing including a radially outer surface, the turbomachine further including an outer annular casing extending over at least a portion of the inner annular casing, the inner annular casing and the outer annular casing defining at least one cavity therebetween, the clearance control system comprising:

a manifold system comprising a plurality of supply tubes disposed within the at least one cavity, the plurality of supply tubes extending circumferentially about the inner annular casing;

an impingement system disposed within the at least one cavity, the impingement system extending circumferentially about the inner annular casing, the plurality of supply tubes configured to channel a flow of a cooling fluid to the impingement system, the impingement system configured to channel the flow of the cooling fluid directly to the radially outer surface of the inner annular casing; and

a plurality of walls disposed within the at least one cavity, wherein the plurality of walls separates the at least one cavity into a first region and a second region, the first region coupled in flow communication with the turbomachine, the plurality of walls is configured to isolate the second region from the first region, the clearance control system disposed within the second region.

19. The clearance control system of claim 18 , wherein the plurality of walls comprises a thermal insulating material.

20. The clearance control system of claim 18 , wherein the manifold system comprises an air valve.

21. The clearance control system of claim 20 , further comprising a controller configured to control a position of the air valve.