Turbine engine adaptive low leakage air seal

Patent metadata

Field	Value
Publication number	US-10119412-B2
Application number	US-201414768769-A
Country	US
Kind code	B2
Filing date	Mar 10, 2014
Priority date	Mar 13, 2013
Publication date	Nov 6, 2018
Grant date	Nov 6, 2018

Abstract

An air seal includes a sealing gland configured to retain a ferro-fluid and one or more seals. A portion of the one or more seals is configured to extend into the sealing gland. A gas turbine engine, includes the air seal. A method of sealing low pressure air from high pressure air, includes the steps of providing a sealing gland configured to retain a ferro-fluid, distributing the ferro-fluid into the sealing gland, providing one or more seals, wherein a portion of the one or more seals is configured to extend into the sealing gland, and removing the ferro-fluid from the sealing gland.

First claim

What is claimed is:

1. A seal, comprising:
a sealing gland configured to retain a ferro-fluid; and
at least one rotating seal, the rotating seal arranged perpendicular to an axis of rotation of a rotating component;
wherein at least a portion of the one or more rotating seals extends into the sealing gland, the sealing gland defined by an annular channel having lateral spaced apart walls, the rotating seal arranged at a location axially between the walls, and
wherein the at least one rotating seal is an airfoil tip seal, and the rotating component is an airfoil blade.

2. The air seal of claim 1 , wherein the sealing gland is subject to a magnetic field.

3. The air seal of claim 1 , wherein the at least one rotating seal is a knife-edge seal.

4. The air seal of claim 1 , wherein the sealing gland extends circumferentially around a rotor, the rotor including the at least one rotating seal.

5. The air seal of claim 1 , further comprising a ferro-fluid collection drain and a ferro-fluid collection tank.

6. The air seal of claim 1 , further comprising a cooler configured to receive the ferro-fluid at a temperature and change the temperature of the ferro-fluid.

7. The air seal of claim 1 , wherein the at least one rotating seal includes a magnetic field configured to repel the ferro-fluid.

8. The air seal of claim 1 , wherein the at least one rotating seal is located on a seal arm extending from a rotating component.

9. A gas turbine engine, comprising:
a combustor section arranged fluidly between a compressor section and a turbine section:
a high pressure area;
a low pressure area, the high and low pressure areas arranged in one of the compressor and turbine sections;
a sealing gland subject to a magnetic field and configured to retain a ferro-fluid; and a rotating component having at least one seal configured to seal the high pressure area from the low pressure area, at least a portion of the at least one seal extending into the sealing gland; and
wherein the at least one rotating seal is a knife edge seal, and the rotating component is one of a turbine and a compressor.

10. The gas turbine engine of claim 9 , wherein the at least one seal is located on a seal arm extending from a rotating component, the seal arranged perpendicular to an axis of rotation of the rotating component.

11. The gas turbine engine of claim 9 , further comprising a cooler configured to receive the ferro-fluid at a temperature and change the temperature of the ferro-fluid.

12. A method of sealing low pressure air from high pressure air in a gas turbine engine, comprising the steps of:
providing a sealing gland configured to retain a ferro-fluid;
distributing the ferro-fluid into the sealing gland;
providing at least one rotating seal, the rotating seal perpendicular to an axis of rotation of a rotating component, wherein at least a portion of the one or more rotating seals extends into the sealing gland, the sealing gland defined by an annular channel having lateral spaced apart walls , the seal arranged at a location axially between the walls;
removing the ferro-fluid from the sealing gland; and
wherein the at least one rotating seal is an airfoil tip seal, and the rotating component is an airfoil blade.

13. The method of claim 12 , wherein the step of distributing the ferro-fluid into the sealing gland further comprises the steps of:
applying an alternating magnetic field to the sealing gland;
allowing the ferro-fluid to form a uniform layer in the sealing gland; and
applying a static magnetic field to the sealing gland.

14. The method of claim 12 , further comprising the step of adjusting the magnetic field to adjust the ferro-fluid to air surface.

15. The method of claim 12 , wherein the ferro-fluid is distributed into the sealing gland during an engine start-up sequence.

16. The method of claim 12 , wherein the ferro-fluid is removed from the sealing gland during engine shut-down.

Assignees

• United Technologies Corp

Inventors

• Roberge Gary D

Classifications

• F01D11/20 Primary

  Actively adjusting tip-clearance · CPC title

• F05D2300/507

  Magnetic properties · CPC title

• F16J15/43

  kept in sealing position by magnetic force · CPC title