Some content of this application is unavailable at the moment.
If this situation persist, please contact us atFeedback&Contact
1. (WO2014137465) GAS TURBINE ENGINE WITH A CLEARANCE CONTROL SYSTEM AND CORRESPONDING METHOD OF OPERATING A GAS TURBINE ENGINE
Note: Text based on automatic Optical Character Recognition processes. Please use the PDF version for legal matters

CLAIMS

WHAT IS CLAIMED IS:

1 . A gas turbine engine, comprising:

a rotor;

at least one of: a bearing system having a bearing with a bearing race

and a bearing internal clearance; a damper system having a damper disposed in a

damper gland and having a damper clearance; and a sealing system having a sealing

component and a seal clearance; and

at least one thermoelectric module configured to achieve a desired value for at least one of the bearing internal clearance, the damper clearance and the seal clearance by changing a diameter of at least one of the bearing race, the damper, the damper gland and the sealing component during operation of the gas turbine engine.

2. The gas turbine engine of claim 1 , wherein the at least one thermoelectric module is configured to change the diameter of the bearing race by selectively heating and cooling the bearing race.

3. The gas turbine engine of claim 1 , wherein the bearing is a rolling element bearing.

4. The gas turbine engine of claim 1 , wherein the bearing is a roller bearing.

5. The gas turbine engine of claim 1 , wherein the bearing race is an outer bearing race.

6. The gas turbine engine of claim 1 , further comprising a bearing housing configured to house the bearing, wherein the at least one thermoelectric module is mounted on or in the bearing housing.

7. The gas turbine engine of claim 1 , wherein the damper is a squeeze film damper configured to damp rotor oscillations based at least in part on a size of the damper clearance.

8. The gas turbine engine of claim 7, wherein the at least one thermoelectric module is configured to eliminate the damper clearance during operation of the gas turbine engine.

9. The gas turbine engine of claim 7, wherein the at least one thermoelectric module is configured to control the damper clearance during operation of the gas turbine engine to achieve a desired damping level.

10. The gas turbine engine of claim 1 , wherein the sealing system is a labyrinth seal system.

1 1 . The gas turbine engine of claim 10, wherein the sealing

component is a stationary seal of the labyrinth seal system.

12. The gas turbine engine of claim 1 , further comprising at least a second thermoelectric module configured to achieve the desired value for at least another of the bearing internal clearance, the damper clearance and the seal clearance by changing a diameter of at least one of the bearing race; the damper, the damper gland and the sealing component during operation of the gas turbine engine.

13. A method for operating a gas turbine engine, comprising:

controlling at least one thermoelectric module to achieve a desired value for at least one of a bearing internal clearance, a damper clearance and a seal clearance by changing a diameter of at least one of a bearing race; a damper, a damper gland and a sealing component during operation of the gas turbine engine.

14. The method of claim 13, further comprising controlling at least one thermoelectric module to reduce the bearing internal clearance by changing the diameter of the bearing race.

15. The method of claim 13, further comprising controlling at least one thermoelectric module to change the diameter of a damping system to eliminate the damper clearance at at least one selected operating point of the gas turbine engine.

16. The method of claim 13, further comprising controlling at least one thermoelectric module to change the diameter of a damping system to achieve a desired damper clearance at at least one selected operating point of the gas turbine engine.

17. The method of claim 13, further comprising controlling the at least one thermoelectric module to change a diameter of a sealing system to reduce the seal clearance at at least one selected operating point of the gas turbine engine.

18. A rotor machine, comprising:

a rotor;

at least one of: a bearing system having a bearing with a bearing race and a bearing internal clearance; a damper system having a damper disposed in a damper gland and having a damper clearance; and a sealing system having a sealing component and a seal clearance; and

means for achieving a desired value for at least one of the bearing internal clearance, the damper clearance and the seal clearance by changing a diameter of at least one of the bearing race, the damper, the damper gland and the sealing component during operation of the rotor machine.

19. The rotor machine of claim 18, wherein the means for achieving a desired value includes at least one thermoelectric module configured to heat at least one of the bearing race, the damper, the damper gland and the sealing component during operation of the rotor machine.

20. The rotor machine of claim 18, wherein the means for achieving a desired value includes at least one thermoelectric module configured to cool at least one of the bearing race, the damper, the damper gland and the sealing component during operation of the rotor machine.