Abradable turbine air seal

Patent metadata

Field	Value
Publication number	US-9598972-B2
Application number	US-74975010-A
Country	US
Kind code	B2
Filing date	Mar 30, 2010
Priority date	Mar 30, 2010
Publication date	Mar 21, 2017
Grant date	Mar 21, 2017

Abstract

An abradable seal for a gas turbine engine includes a metal alloy and a plurality of pores in the metal alloy. The plurality of pores have a diameter of approximately 1 to 10 microns.

First claim

What is claimed is:

1. An abradable seal for a gas turbine engine comprising:
a metal alloy, wherein the metal alloy is MCrAlY, and M is a metal, Cr is chromium, Al is aluminum and Y is yttrium; and
a plurality of pores in the metal alloy, wherein the plurality of pores have a diameter of approximately 1 to 10 microns.

2. The abradable seal as recited in claim 1 wherein approximately 30 to 50% of an abradable seal is the metal alloy and approximately 50 to 70% of the abradable seal is the plurality of pores.

3. The abradable seal as recited in claim 1 wherein the metal is one of nickel and cobalt.

4. The abradable seal as recited in claim 1 wherein a fugitive filler is mixed with the metal alloy, and the fugitive filler is burned away to form the plurality of pores.

5. The abradable seal as recited in claim 4 wherein the fugitive filler is one of polymethylmethacrylate, polyester, and polyvinyl chloride.

6. The abradable seal as recited in claim 4 wherein the metal alloy is refined to a size of 1 to 25 microns and the fugitive filler is refined to a size of 0.5 to 25 microns prior to formation of an abradable seal.

7. The abradable seal as recited in claim 1 wherein the metal alloy and a fugitive filler are applied simultaneously to the component of the gas turbine engine.

8. A gas turbine engine comprising:
a compressor to compress air, wherein the compressor includes alternating rows of rotating compressor blades and static vanes;
a casing to house at least the compressor; and
an abradable seal on an inner surface of the casing, wherein tips of the rotating compressor blades engage the abradable seal, the abradable seal includes a metal alloy and a plurality of pores in the metal alloy, the metal alloy is MCrAlY, M is a metal, Cr is chromium, Al is aluminum and Y is yttrium, and the plurality of pores have a diameter of approximately 1to 10 microns.

9. The gas turbine engine as recited in claim 8 wherein a fugitive filler is mixed with the metal alloy, and the fugitive filler is burned away to form the plurality of pores, and the fugitive filler is one of polymethylmethacrylate, polyester, and polyvinyl chloride.

10. The gas turbine engine as recited in claim 9 wherein the metal alloy is refined to a size of 1 to 25 microns and the fugitive filler is refined to a size of 0.5 to 25 microns prior to formation of an abradable seal.

11. The gas turbine engine as recited in claim 8 including an abradable inner air seal on a free end of the plurality of static vanes.

12. The gas turbine engine as recited in claim 11 including a projection on a rotor shaft that engages the abradable inner air seal.

13. A method of forming an abradable seal for a gas turbine engine, the method comprising the steps of:
applying an abradable seal to a component of a gas turbine engine, wherein the abradable seal includes a metal alloy and a plurality of pores in the metal alloy, wherein the plurality of pores have a diameter of approximately 1 to 10 microns, the metal alloy is MCrAlY, and M is a metal, Cr is chromium, Al is aluminum and Y is yttrium.

14. The method as recited in claim 13 wherein the abradable seal is applied by thermal spraying.

15. The method as recited in claim 14 including the step of adding a fugitive filler to the metal alloy.

16. The method as recited in claim 15 wherein the abradable seal is heated to a temperature between 400 and 900° F. to melt and burn away the fugitive filler to form the plurality of pores in the metal alloy.

17. The method as recited in claim 15 including the step of machining the metal alloy and the fugitive filler prior to the step of applying to reduce a particle size.

18. The method as recited in claim 15 including a step of refining the metal alloy to have a particle size of 1 to 25 microns and a step of refining the fugitive filler to have a particle size of 0.5 to 25 microns before the step of applying the abradable seal.

19. The method as recited in claim 13 wherein the abradable seal is applied by a foaming metal process.

20. The method as recited in claim 13 wherein the abradable seal is applied by a powder metallurgy process.

Assignees

• Strock Christopher W
• United Technologies Corp

Inventors

• Strock Christopher W

Classifications

• Y10T29/4932

  Turbomachine making · CPC title

• F01D11/122 Primary

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

• F05D2300/43

  Synthetic polymers, e.g. plastics; Rubber · CPC title

• F05D2300/514

  Porosity · CPC title

• F05D2300/612

  Foam · CPC title