Systems and methods for dynamically sealing a turbine engine

Patent metadata

Field	Value
Publication number	US-9488060-B2
Application number	US-201314049967-A
Country	US
Kind code	B2
Filing date	Oct 9, 2013
Priority date	Oct 9, 2013
Publication date	Nov 8, 2016
Grant date	Nov 8, 2016

Abstract

A turbine engine assembly is provided. The turbine engine assembly includes a stator assembly and a rotor assembly having a rotor disk coupled to a plurality of rotor blades, the plurality of rotor blades extending radially outward from the rotor disk. The assembly also includes a casing that at least partially circumscribes the plurality of rotor blades. The assembly also includes a dynamic sealing device coupled to the stator assembly. The at least one dynamic sealing device is configured to insert a seal between the casing and the plurality of rotor blades to facilitate reducing a clearance gap defined between the plurality of rotor blades and the casing while the rotor assembly is operating.

First claim

What is claimed is:

1. A turbine engine assembly comprising:
a stator assembly;
a rotor assembly comprising a rotor disk coupled to a plurality of rotor blades, said plurality of rotor blades extending radially outward from said rotor disk;
a casing extending at least partially about said plurality of rotor blades to define a clearance gap; and
a dynamic sealing device comprising a rotatable shaft, a spool coupled to said shaft, and a seal coupled to said spool, said dynamic sealing device for selectively rotating said shaft to unwind said seal from said spool for inserting said seal between said casing and said plurality of rotor blades to facilitate reducing the clearance gap defined between said plurality of rotor blades and said casing while said rotor assembly is operating.

2. The turbine engine assembly of claim 1 , wherein said dynamic sealing device is operable to selectively rotate said shaft to wind said seal about said spool for removing said seal from between the casing and the plurality of rotor blades to facilitate increasing the clearance gap while said rotor assembly is operating.

3. The turbine engine assembly of claim 1 , further comprising a controller and a sensor that measures at least one characteristic of said rotor assembly, said controller configured to:
determine an operational status of said rotor assembly based on the at least one characteristic; and
instruct said dynamic sealing device to insert said seal during a predefined operating condition of said rotor assembly.

4. The turbine engine assembly of claim 3 , wherein said controller is further configured to instruct said dynamic sealing device to remove said seal during a second predefined operating condition of said rotor assembly.

5. The turbine engine assembly of claim 1 , wherein said casing comprises an inner surface that defines a retaining groove, said retaining groove sized to receive said seal therein.

6. The turbine engine assembly of claim 1 further comprising a plurality of dynamic sealing devices, wherein a first dynamic sealing device is coupled to a first end of said seal and a second dynamic sealing device is coupled to a second end of said seal.

7. The turbine engine assembly of claim 1 further comprising a mold coupled to said dynamic sealing device for reshaping a cross-sectional profile of said seal from a first cross-sectional profile to a second cross-sectional profile.

8. A dynamic sealing device for use in a turbine engine having a plurality of rotor blades and a casing extending at least partially about the plurality of rotor blades to define a clearance gap, said dynamic sealing device comprising a rotatable shaft, a spool coupled to said shaft, and a seal coupled to said spool, said dynamic sealing device for selectively rotating said shaft to unwind said seal from said spool for inserting, during operation of the turbine engine, said seal between the plurality of rotor blades and the casing to facilitate reducing the clearance gap defined between the plurality of rotor blades and the casing.

9. The dynamic sealing device of claim 8 , wherein said seal is at least in part flexible.

10. The dynamic sealing device of claim 8 , wherein said dynamic sealing device is operable to selectively rotate said shaft to wind said seal about said spool for removing said seal from between the casing and the plurality of rotor blades to facilitate increasing the clearance gap during operation of the turbine engine.

11. The dynamic sealing device of claim 8 , wherein said seal comprises a first end, a second end, and a body between said first end and said second end, wherein said first end is coupled to said spool and wherein said body is insertable between the plurality of rotor blades and the casing.

12. The dynamic sealing device of claim 8 , wherein the casing defines a retaining groove, said seal being insertable into the retaining groove.

13. The dynamic sealing device of claim 12 , wherein said seal has a substantially T-shaped cross-sectional profile when said seal is inserted into the retaining groove, said profile including a radially inner portion, a radially outer portion, and a neck portion extending between said radially inner portion and said radially outer portion.

14. The dynamic sealing device of claim 8 further comprising a mold for reshaping a cross-sectional profile of said seal from a first cross-sectional profile to a second cross-sectional profile.

15. A method for facilitating sealing a turbine engine, said method comprising:
rotating a shaft to unwind a seal from a spool of a dynamic sealing device; and
inserting the unwound seal between a plurality of rotor blades and a casing of the turbine engine while the turbine engine is operating, such that the seal facilitates reducing a clearance gap defined between the plurality of rotor blades and the casing.

16. The method of claim 15 further comprising selectively rotating the shaft to wind the seal about the spool for removing, with the dynamic sealing device, the seal from between the casing and the plurality of rotor blades to facilitate increasing the clearance gap during operation of the turbine engine.

17. The method of claim 15 further comprising:
determining, with a controller that is communicatively coupled to the dynamic sealing device, an operational status of the turbine engine; and
inserting the seal when the turbine engine is in a predefined operating condition.

18. The method of claim 17 , wherein inserting the seal when the turbine engine is in a predefined operating condition includes inserting the seal when the turbine engine is in a steady-state operating condition.

19. The method of claim 15 further comprising:
determining, with a controller that is communicatively coupled to the dynamic sealing device, an operational status of the turbine engine; and
removing the seal when the turbine engine is in one of a start-up operating condition, a shut-down operating condition, and a transient operating condition.

20. The method of claim 15 further comprising:
receiving, by a controller communicatively coupled to the dynamic sealing device, an instruction to remove the seal;
removing, with the dynamic sealing device, the seal from between the casing and the plurality of rotor blades; and
replacing the seal with a new seal.

Assignees

• Gen Electric

Inventors

• Bowman Michael John

Classifications

• F01D11/22

  by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor · CPC title

• F01D11/122 Primary

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F16J15/445

  with means for adjusting the clearance · CPC title

• Y10T29/49316

  Impeller making · CPC title