Turbine components with passive cooling pathways

Patent metadata

Field	Value
Publication number	US-9617859-B2
Application number	US-201213645729-A
Country	US
Kind code	B2
Filing date	Oct 5, 2012
Priority date	Oct 5, 2012
Publication date	Apr 11, 2017
Grant date	Apr 11, 2017

Abstract

The present application provides a turbine component for use in a hot gas path of a gas turbine. The turbine component may include an outer surface, an internal cooling circuit, a number of cooling pathways in communication with the internal cooling circuit and extending through the outer surface, and a number of adaptive cooling pathways in communication with the internal cooling circuit and extending through the outer surface. The adaptive cooling pathways may include a high temperature compound therein.

First claim

We claim:

1. A turbine component for use in a hot gas path of a gas turbine, comprising:
an outer surface;
an internal cooling circuit;
a plurality of cooling pathways in communication with the internal cooling circuit, wherein the plurality of cooling pathways comprises inner walls that define a hollow portion of the plurality of cooling pathways;
a plurality of cooling trenches in communication with the plurality of cooling pathways and the outer surface, wherein the plurality of cooling trenches comprises a conical portion; and
a high temperature compound positioned in and adhered to walls forming the plurality of cooling trenches such that the plurality of cooling trenches is at least partially filled, wherein the high temperature compound blocks a path from an end of the hollow portion of the plurality of cooling pathways to the outer surface, and wherein the plurality of cooling pathways is void of the high temperature compound, the high temperature compound configured to blowout of the conical portion at a predetermined burnout temperature.

2. The turbine component of claim 1 , wherein the turbine component comprises an airfoil.

3. The turbine component of claim 2 , wherein the airfoil comprises a blade or a vane.

4. The turbine component of claim 1 , wherein the plurality of cooling pathways comprises a plurality of cooling holes with a cylindrical configuration.

5. The turbine component of claim 1 , wherein the high temperature compound turns to ash at the predetermined burnout temperature.

6. The turbine component of claim 1 , wherein the high temperature compound is configured to blowout due to a pressure differential across the plurality of cooling trenches.

7. The turbine component of claim 1 , wherein the plurality of cooling pathways comprises a plurality of adaptive cooling holes.

8. The turbine component of claim 1 , further comprising a cooling medium flowing through the internal cooling circuit.

9. The turbine component of claim 8 , wherein the cooling medium flows through the plurality of cooling pathways.

10. The turbine component of claim 8 , further comprising a supplemental volume of the cooling medium and wherein the supplement volume of the cooling medium flows through the plurality of cooling pathways once a local predetermined temperature is reached.

11. The turbine component of claim 1 , wherein the turbine component comprises a shank.

12. The turbine component of claim 1 , wherein the conical portion is oriented such that a volume of the conical portion increases from the hollow portion to the outer surface.

13. The turbine component of claim 1 , wherein a first number of the plurality of cooling pathways is equal to a second number of the plurality of cooling trenches.

14. A method of cooling a turbine component operating in a hot gas path, comprising:
flowing a coolant through an internal cooling circuit;
flowing the coolant through a plurality of cooling pathways in an outer surface, wherein the plurality of cooling pathways comprises inner walls that define a hollow portion of the plurality of cooling pathways;
blocking a path from the internal cooling circuit to the outer surface with a high temperature compound, wherein the high temperature compound is positioned such that a plurality of cooling trenches is at least partially filled, and wherein the plurality of cooling pathways is void of the high temperature compound;
heating the high temperature compound in a conical portion of one or more adaptive cooling trenches once a local predetermined temperature is reached;
creating a pressure differential across the one or more adaptive cooling trenches;
ashing out the high temperature compound; and
flowing a supplemental volume of the air through the one or more cooling pathways.

15. An airfoil component for use in a hot gas path of a gas turbine, comprising:
an outer surface;
a plurality of internal cooling circuits;
a plurality of cooling pathways in communication with the plurality of internal cooling circuits, wherein the plurality of cooling pathways is hollow and comprises inner walls that define a hollow portion of the plurality of cooling pathways; and
a plurality of adaptive cooling trenches in communication with the plurality of cooling pathways and extending through the outer surface wherein the plurality of cooling trenches comprises a conical portion at least partially filled with a high temperature compound that blocks a path from the internal cooling circuit to the outer surface, and wherein the plurality of cooling pathways is void of the high temperature compound, the high temperature compound configured to pop out of the conical portion at a predetermined burnout temperature.

16. The airfoil component of claim 15 , wherein the high temperature compound oxidizes at a predetermined temperature.

17. The airfoil component of claim 15 , wherein the high temperature compound softens or changes volumetrically at a predetermined temperature.

18. The airfoil component of claim 15 , further comprising a cooling medium flowing through the plurality of cooling pathways and further comprising a supplemental volume of the cooling medium flowing through the plurality of adaptive cooling trenches once a local predetermined temperature is reached.

Assignees

• Gen Electric

Inventors

• Morgan Victor John
• Pope Stephen Gerard
• Kittleson Jacob
• Levy Lawrence Matthew

Classifications

• F05D2300/611

  Coating · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D5/187

  Convection cooling · CPC title

• F05D2230/50

  Building or constructing in particular ways · CPC title