Hybrid airfoil cooling

Patent metadata

Field	Value
Publication number	US-10428660-B2
Application number	US-201715420882-A
Country	US
Kind code	B2
Filing date	Jan 31, 2017
Priority date	Jan 31, 2017
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

An airfoil may comprise an airfoil body having a leading edge and a trailing edge. A heat pipe may be disposed within the airfoil. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be disposed within the airfoil body and may be configured to remove heat from the trailing edge. The second cooling apparatus may be disposed within the airfoil body and may be configured to remove heat from the leading edge.

First claim

What is claimed is:

1. An airfoil, comprising:
an airfoil body having a leading edge and a trailing edge;
a heat pipe disposed within the airfoil, the heat pipe including a vaporization section and a condensation section, the vaporization section disposed within the airfoil body and configured to remove heat from the trailing edge; and
a second cooling apparatus disposed within the airfoil body and configured to remove heat from the leading edge,
wherein the condensation section is disposed radially outward from the airfoil body and in a path of a cooling airflow, and
wherein the second cooling apparatus comprises a cooling chamber defining a cooling path within the airfoil body, the cooling path configured to receive the cooling airflow.

2. The airfoil of claim 1 , wherein the vaporization section comprises a plurality of tabs extending toward the trailing edge.

3. The airfoil of claim 2 , wherein the plurality of tabs are in contact with an inner surface of the airfoil body.

4. The airfoil of claim 3 , wherein the plurality of tabs comprise a thermally conductive material and are configured to conduct heat away from the trailing edge.

5. The airfoil of claim 4 , wherein the plurality of tabs are spaced radially along the trailing edge.

6. The airfoil of claim 5 , wherein the trailing edge comprises a knife edge.

7. A gas turbine engine, comprising:
a turbine section having a core flowpath and a cooling airflow;
an airfoil having an airfoil body disposed in the core flowpath, the airfoil body having a leading edge and a trailing edge;
a heat pipe disposed within the airfoil, the heat pipe including a vaporization section and a condensation section, the vaporization section disposed within the airfoil body and the condensation section disposed in the cooling airflow; and
a second cooling apparatus disposed within the airfoil body and configured to receive the cooling airflow,
wherein the condensation section is disposed radially outward from the airfoil body and in a path of the cooling airflow, and
wherein the second cooling apparatus comprises a cooling chamber defining a cooling path within the airfoil body, the cooling path configured to receive the cooling airflow.

8. The gas turbine engine of claim 7 , wherein the heat pipe is configured to remove heat from the trailing edge and the second cooling apparatus is configured to remove heat from the leading edge.

9. The gas turbine engine of claim 7 , wherein the vaporization section comprises a plurality of tabs extending toward the trailing edge.

10. The gas turbine engine of claim 9 , wherein the plurality of tabs are in contact with an inner surface of the airfoil body.

11. The gas turbine engine of claim 9 , wherein the plurality of tabs comprise a thermally conductive material and are configured to conduct heat away from the trailing edge.

12. The gas turbine engine of claim 10 , wherein the trailing edge comprises a knife edge.

13. The gas turbine engine of claim 7 , further comprising a compressor section, wherein the cooling airflow is bled from the compressor section and directed to the condensation section of the heat pipe.

14. A method of cooling an airfoil, comprising,
disposing a vaporization section of a heat pipe within an airfoil body of the airfoil at a trailing edge;
disposing a condensation section of the heat pipe radially outward from the airfoil;
defining a second cooling feature within the airfoil, the second cooling feature configured to remove heat from a leading edge of the airfoil; and
directing a cooling airflow around the condensation section and into the second cooling feature.

15. The method of claim 14 , wherein the vaporization section includes a plurality of tabs extending toward the trailing edge.

16. The method of claim 15 , wherein the heat pipe is configured to remove heat from the trailing edge of the airfoil.

Assignees

• United Technologies Corp

Inventors

• Hill James D
• Ranjan Ram
• Levasseur Glenn

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title