Airfoil cooling device and method of manufacture

Patent metadata

Field	Value
Publication number	US-9932835-B2
Application number	US-201514698269-A
Country	US
Kind code	B2
Filing date	Apr 28, 2015
Priority date	May 23, 2014
Publication date	Apr 3, 2018
Grant date	Apr 3, 2018

Abstract

An airfoil has an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure. A swirl structure is operatively associated with the cooling passage and configured to impart a tangential velocity to the cooling medium flowing through the cooling passage. An airfoil has an airfoil structure that defines a first cooling passage and a second cooling passage for directing cooling medium through the airfoil structure, each cooling passage having a swirl structure that imparts tangential velocity on the cooling medium flowing through the associated cooling passage. A method of making an airfoil that includes forming an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure and forming a swirl structure that is operatively associated with the cooling passage and imparts tangential velocity to the cooling medium flowing through the cooling passage.

First claim

The invention claimed is:

1. An airfoil, comprising:
a concave pressure wall;
a convex suction wall;
a cooling channel extending between the concave pressure wall and the convex suction wall;
a cavity, wherein at least a portion of the cavity is bounded by at least one of the concave pressure wall and the convex suction wall;
an airfoil structure forming at least a portion of a boundary between the cooling channel and the cavity and defining a cooling passage extending therethrough, wherein the cooling passage is configured to direct a cooling medium from the cooling channel onto a surface of the cavity; and
a swirl structure operatively associated with the cooling passage and configured to impart tangential velocity to the cooling medium, wherein the swirl structure is at least partially within the cooling passage.

2. The airfoil of claim 1 , wherein the swirl structure is completely within the cooling passage.

3. The airfoil of claim 1 , wherein the swirl structure comprises a protrusion extending from at least one surface of the cooling passage.

4. The airfoil of claim 3 , wherein the swirl structure is generally a spiral ramp.

5. The airfoil of claim 1 , wherein the swirl structure comprises a partition extending from at least one surface of the cooling passage, and wherein the partition divides the cooling passage into a plurality of volumes through which the cooling medium can flow.

6. The airfoil of claim 5 , wherein the swirl structure is generally a helicoid.

7. The airfoil of claim 1 , wherein the swirl structure has between a quarter twist and four twists about an axis extending between an inlet and an outlet of the cooling passage.

8. The airfoil of claim 1 , wherein the swirl structure has a straight portion and a twisting portion, and wherein the straight portion is located upstream of the twisting portion.

9. The airfoil of claim 1 , wherein the cooling passage is configured to direct cooling medium on to an interior surface of a leading edge of the airfoil.

10. The airfoil of claim 1 , wherein the swirl structure imparts tangential velocity to the cooling medium that is 10% to 80% of an absolute velocity of the cooling medium flowing through the cooling passage.

11. An airfoil, comprising:
a concave pressure wall;
a convex suction wall;
a cooling channel extending between the concave pressure wall and the convex suction wall;
a cavity, wherein at least a portion of the cavity is bounded by at least one of the concave pressure wall and the convex suction wall;
an airfoil structure forming at least a portion of a boundary between the cooling channel and the cavity and defining a first cooling passage and a second cooling passage, wherein each of the first cooling passage and the second cooling passage extends through the airfoil structure and is configured to direct a cooling medium from the cooling channel onto a surface of the cavity;
a first swirl structure operatively associated with the first cooling passage and configured to impart tangential velocity to the cooling medium, wherein the first swirl structure is at least partially within the first cooling passage;
a second swirl structure operatively associated with the second cooling passage and configured to impart tangential velocity to the cooling medium, wherein the second swirl structure is at least partially within the second cooling passage, and wherein the first and second cooling passages each have a hydraulic diameter and a centerline axis, and wherein a span between the first and second cooling passages is measured between the centerline axes of each cooling passage, and wherein a ratio of the span between cooling passages divided by the hydraulic diameter of the cooling passages is between 1.5 and 8.

12. A method of manufacturing an airfoil, the method comprising:
forming a cooling channel between a concave pressure wall and a convex suction wall;
forming a cavity, wherein at least a portion of the cavity is bounded by at least one of the concave pressure wall and the convex suction wall;
forming an airfoil structure that forms at least a portion of a boundary between the cooling channel and the cavity;
forming a cooling passage that extends through the airfoil structure and is configured to direct a cooling medium from the cooling channel onto a surface of the cavity; and
forming a swirl structure operatively associated with the cooling passage and configured to impart tangential velocity to the cooling medium, wherein the swirl structure is formed at least partially within the cooling passage.

13. The method of claim 12 , wherein the swirl structure is formed completely within the cooling passage.

14. The method of claim 12 , wherein the swirl structure forms a protrusion extending from at least one surface of the cooling passage.

15. The method of claim 12 , wherein the swirl structure forms a partition extending from at least one surface of the cooling passage, and wherein the partition divides the cooling passage into a plurality of volumes through which cooling medium flows.

16. The method of claim 12 , wherein the swirl structure has between a quarter twist and four twists about an axis extending between an inlet and an outlet of the cooling passage.

17. The method of claim 12 , wherein the swirl structure is configured to impart to the cooling medium a tangential velocity that is 10% to 80% of an absolute velocity of the cooling medium flowing through the cooling passage.

18. The method of claim 12 , the method further comprising:
creating a three-dimensional computer model of a casting core for an airfoil, the casting core comprising:
an airfoil structure body configured to form the airfoil structure and the cooling passage; and
a swirl structure body configured to form the swirl structure that is operatively associated with the cooling passage and configured to impart tangential velocity to the cooling medium flowing therethrough;

forming a casting core, wherein the casting core is formed in progressive layers by selectively curing a ceramic-loaded resin with ultraviolet light; and
processing the casting core thermally, wherein the casting core is suitable for casting.

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Martin Thomas J
• Snyder Brooks E

Classifications

• 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

• F05D2230/22

  by sintering · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2250/25

  helical · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title