Hot gas path component for turbine system

Patent metadata

Field	Value
Publication number	US-10100666-B2
Application number	US-201313853556-A
Country	US
Kind code	B2
Filing date	Mar 29, 2013
Priority date	Mar 29, 2013
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough.

First claim

What is claimed is:

1. A hot gas path component for a turbine system, comprising:
a shell having an exterior surface and an interior surface; and
a porous media having an exterior surface and an interior surface, the porous media including varying permeability in one of an axial direction, a circumferential direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media positioned in contact with the shell,
wherein the porous media directionally controls a cooling medium flowing therethrough in one of an axial direction, a circumferential direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction.

2. The hot gas path component of claim 1 , wherein the porous media includes a plurality of porous media inserts each including varying permeability to a cooling medium flowing therethrough.

3. The hot gas path component of claim 1 , wherein the exterior surface of the porous media is positioned in contact with the interior surface of the shell.

4. The hot gas path component of claim 3 , further comprising an impingement sleeve positioned in contact with the interior surface of the porous media.

5. The hot gas path component of claim 3 , wherein the interior surface of the porous media is treated by at least one of grinding, filling, brazing, welding, soldering, and coating to seal the interior surface of the porous media.

6. The hot gas path component of claim 1 , wherein the interior surface of the porous media is positioned in contact with the exterior surface of the shell.

7. The hot gas path component of claim 6 , wherein the interior surface of the porous media is in contact with the exterior surface of the shell.

8. The hot gas path component of claim 6 , wherein the exterior surface of the porous media is treated by coating with a coating layer to seal the exterior surface of the porous media.

9. The hot gas path component of claim 1 , wherein the porous media is formed from one of a metal foam, a ceramic foam, or a carbon fiber foam.

10. The hot gas path component of claim 1 , wherein the hot gas path component is a nozzle.

11. A hot gas path component for a turbine system, comprising:
a shell having an exterior surface and an interior surface; and
a porous media having an exterior surface and an interior surface, the porous media including varying permeability along one of a minor axis, a thickness of the porous media, a major axis and through a thickness of the porous media, a minor axis and through a thickness of the porous media, a major axis and a minor axis, or a major axis, a minor axis and through a thickness of the porous media, the porous media positioned in contact with the shell,
wherein the porous media directionally controls a cooling medium flowing therethrough along one of a minor axis, through a thickness of the porous media, a major axis and through a thickness of the porous media, minor axis and through a thickness of the porous media, a major axis and a minor axis, or a major axis, a minor axis and through a thickness of the porous media.

12. A turbine system, comprising:
a compressor;
a turbine coupled to the compressor; and
a plurality of hot gas path components disposed in at least one of the compressor or the turbine, at least one of the hot gas path components comprising:
a shell having an exterior surface and an interior surface; and
a porous media having an exterior surface and an interior surface, the porous media including varying permeability in one of an axial direction, a circumferential direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media positioned in contact with the shell,
wherein in the porous media directionally controls a cooling medium flowing therethrough in one of an axial direction, a circumferential direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction.

13. The turbine system of claim 12 wherein the porous media include a plurality of porous media inserts each including varying flow resistance in one or more of the axial direction, the circumferential direction, the axial and the radial direction, the axial and the circumferential direction the radial and the circumferential direction or the axial, the radial and the circumferential direction.

14. The turbine system of claim 12 , wherein the exterior surface of the porous media is positioned in contact with the interior surface of the shell.

15. The turbine system of claim 12 , wherein the interior surface of the porous media is positioned in contact with the exterior surface of the shell.

16. The turbine system of claim 12 , further comprising an impingement sleeve positioned in contact with the porous media.

17. The turbine system of claim 12 , wherein a surface of the porous media is treated by at least one of grinding, filling, brazing, welding, soldering, and coating to seal the surface of the porous media.

18. The turbine system of claim 12 , wherein the hot gas path component is a nozzle.

19. The turbine system of claim 12 , wherein the porous media is formed from one of a metal foam, a ceramic foam, or a carbon fiber foam.

Assignees

• Gen Electric

Inventors

• Brzek Brian Gene
• Morgan Victor John
• Lacy Benjamin Paul

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/183 Primary

  Blade walls being porous · CPC title

• F01D9/02

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

• F01D25/12 Primary

  Cooling · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic