Cooling structure for a turbine component

Patent metadata

Field	Value
Publication number	US-10400608-B2
Application number	US-201615360529-A
Country	US
Kind code	B2
Filing date	Nov 23, 2016
Priority date	Nov 23, 2016
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween.

First claim

What is claimed is:

1. A tip cooling apparatus for a turbine airfoil, comprising: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween, wherein the plurality of interior passages are configured to define cubic repeating modules.

2. The apparatus of claim 1 wherein the outlet surface is coextensive with a tip surface defined by the tip walls.

3. The apparatus of claim 1 wherein the pocket is formed within a thickness of one or both of the tip walls.

4. The apparatus of claim 1 where the pocket is defined between the tip walls.

5. The apparatus of claim 1 wherein the outlets have a diameter of about 0.002 to about 0.005 inches.

6. The apparatus of claim 1 wherein a plenum is defined between the inlet surface of the cooling matrix and the pocket.

7. The apparatus of claim 1 wherein the plurality of interior passages comprise a plurality of tubes interconnected by a plurality of hubs.

8. The apparatus of claim 7 wherein two or more of the plurality of tubes intersecting a given one of the plurality of hubs are not aligned coaxially with each other.

9. The apparatus of claim 1 where the plurality of interior passages comprise a helical configuration.

10. The apparatus of claim 1 wherein the plurality of interior passages comprise a single helix.

11. The apparatus of claim 1 where the plurality of interior passages comprise a double helix.

12. The apparatus of claim 9 wherein the helix shapes include hubs at their intersections.

13. The apparatus of claim 1 wherein a plurality of recesses are formed in the outlet surface, and at least some of the outlets intersect the recesses.

14. The apparatus of claim 13 wherein the plurality of recesses comprise a series of spaced-apart grooves.

15. The apparatus of claim 13 wherein the plurality of recesses comprise dimples.

16. A turbine blade, comprising: a dovetail; a blade shank extending from the dovetail and terminating in a platform that projects laterally outwardly from and surrounds the shank; and an airfoil extending from the platform, the airfoil including: a root, a tip, a leading edge, a trailing edge, a pressure side wall and a suction side wall, and an internal cavity, said internal cavity being bounded at its radially outer end by a tip cap; a squealer tip comprising spaced-apart tip walls extending above said tip cap; a cooling matrix disposed outboard of the tip cap, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the interior cavity, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween, wherein the plurality of interior passages are configured to define cubic repeating modules.

17. The turbine blade of claim 16 wherein the outlet surface is coextensive with a tip surface of the airfoil defined by the walls of the squealer tip.

18. The turbine blade of claim 16 wherein a plenum is defined between the inlet surface and the tip cap.

19. The turbine blade of claim 16 wherein a plurality of recesses are formed in the outlet surface, and at least some of the outlets intersect the recesses.

20. A turbine component, comprising: a flowpath wall defining a flowpath surface configured to be exposed in operation to a hot gas flow, the flowpath wall having a backside opposite to the flowpath surface which forms part of the boundary of an internal cooling circuit of the component; a pocket defined within the flowpath wall; at least one feed hole formed in the flowpath wall communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween, wherein the plurality of interior passages are configured to define cubic repeating modules.

21. The turbine component of claim 20 wherein the outlet surface is coextensive with the flowpath surface.

22. The turbine component of claim 20 wherein a plenum is defined between the inlet surface of the cooling matrix and the pocket.

Assignees

• Gen Electric

Inventors

• Coomer Jessica Elizabeth
• Beyer Matthew Thomas
• Molter Stephen
• Smith Aaron Ezekiel

Classifications

• F05D2260/204

  by the use of microcircuits · CPC title

• F05D2260/203

  by transpiration cooling · CPC title

• F05D2250/25

  helical · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title