Airfoil and method of making

Patent metadata

Field	Value
Publication number	US-9551228-B2
Application number	US-201313737200-A
Country	US
Kind code	B2
Filing date	Jan 9, 2013
Priority date	Jan 9, 2013
Publication date	Jan 24, 2017
Grant date	Jan 24, 2017

Abstract

An airfoil includes leading and trailing edges, a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces, a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces, and cavities within the airfoil. A first cavity extends along the inner surface of the first exterior wall and a first inner wall and has an upstream end and a downstream end, and a feed cavity is located between the first inner wall and the second exterior wall.

First claim

The invention claimed is:

1. An airfoil comprising:
leading and trailing edges;
a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces;
a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces;
a first cavity extending along the inner surface of the first exterior wall and a first inner wall, the first cavity having an upstream end and a downstream end, wherein the first cavity comprises:
a first plenum near one of the upstream and downstream ends of the first cavity; and
a region near the end of the first cavity opposite the first plenum for receiving a cooling fluid; and

a feed cavity located between the first inner wall and the second exterior wall.

2. The airfoil of claim 1 , further comprising:
an impingement cavity in fluid communication with the feed cavity, the impingement cavity comprising a plurality of cooling holes on or near the leading edge.

3. The airfoil of claim 1 , further comprising:
a plurality of cooling holes extending through the first exterior wall and in communication with the first plenum, wherein the first plenum comprises a backstrike region for allowing holes to be drilled into the first exterior wall.

4. The airfoil of claim 1 , further comprising:
a second cavity extending along the inner surface of the second exterior wall and a second inner wall, the second cavity having an upstream end and a downstream end, wherein the second inner wall separates the second cavity from the feed cavity.

5. The airfoil of claim 4 , wherein the second cavity comprises:
a second plenum near one of the upstream and downstream ends of the second cavity; and
a region near the end of the second cavity opposite the second plenum for receiving a cooling fluid.

6. The airfoil of claim 5 , further comprising:
a plurality of cooling holes extending through the second exterior wall and in communication with the second plenum, wherein the second plenum comprises a backstrike region for allowing holes to be drilled into the second exterior wall.

7. An airfoil comprising:
leading and trailing edges;
a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces;
a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces;
a first cavity extending along the inner surface of the first exterior wall and a first inner wall, the first cavity having an upstream end and a downstream end;
a feed cavity located between the first inner wall and the second exterior wall; and
a second cavity extending along the inner surface of the second exterior wall and a second inner wall, the second cavity having an upstream end and a downstream end, wherein the second inner wall separates the second cavity from the feed cavity,
wherein at least one of the first and second cavities extends across an airfoil camber line.

8. The airfoil of claim 7 , wherein both of the first and second cavities extend across the airfoil camber line.

9. An airfoil comprising:
leading and trailing edges;
a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces;
a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces;
a first cavity extending along the inner surface of the first exterior wall and a first inner wall, the first cavity having an upstream end and a downstream end;
a feed cavity located between the first inner wall and the second exterior wall;
a second cavity extending along the inner surface of the second exterior wall and a second inner wall, the second cavity having an upstream end and a downstream end, wherein the second inner wall separates the second cavity from the feed cavity;
a third cavity extending along the inner surface of at least one of the first and second exterior walls; and
a plurality of cooling holes extending through at least one of the first and second exterior walls in communication with the third cavity.

10. A method of forming an airfoil, the method comprising:
forming a first ceramic core comprising:
a first side having a first length; and
a second side generally opposite the first side and having a second length;

forming a second ceramic core having a length generally greater than or equal to the first length, wherein the second ceramic core comprises an upstream region, an intermediate region and a downstream region, and wherein the second ceramic core is formed so that the upstream and downstream regions each have a greater lateral thickness than the intermediate region, and wherein the first internal cooling circuit of the cast airfoil has upstream and downstream regions each with a greater lateral thickness than the intermediate region;
forming a core assembly comprising:
positioning the second ceramic core so that it is proximate but spaced from the first side of the first ceramic core;

casting the airfoil using the core assembly to provide the airfoil with a central core passage and a first internal cooling circuit located on one side of the central core passage, wherein the first internal cooling circuit has a length generally greater than or equal to a length of the side of the central core passage proximate to the first internal cooling circuit.

11. The method of claim 10 , further comprising:
forming a third ceramic core having a length generally greater than or equal to the second length, and wherein forming the core assembly further comprises positioning the third ceramic core so that it is proximate but spaced from the second side of the first ceramic core, and wherein casting the airfoil provides the airfoil with a second internal cooling circuit located on a side of the central core passage generally opposite the first internal cooling circuit, and wherein the second internal cooling circuit has a length generally greater than or equal to a length of the side of the central core passage proximate to the second internal cooling circuit.

12. The method of claim 10 , further comprising:
forming a fourth ceramic core; and
positioning the fourth ceramic core upstream of the third ceramic core in the core assembly in order to provide the airfoil with an impingement cavity upon casting.

13. The method of claim 12 , further comprising:
drilling a cooling hole through an exterior wall of the airfoil and into the upstream region of the first internal cooling circuit.

14. The method of claim 11 , wherein the third ceramic core comprises an upstream region, an intermediate region and a downstream region, and wherein the third ceramic core is formed so that the upstream and downstream regions each have a greater lateral thickness than the intermediate region, and wherein the second internal cooling circuit of the cast airfoil has upstream and downstream regions each with a greater lateral thickness than the intermediate region.

15. The method of claim 14 , further comprising:
drilling a cooling hole through an exterior wall of the airfoil and into the upstream region of the second internal cooling circuit.

16. A method of forming an airfoil, the method comprising:
forming a first ceramic core comprising: a first side having a first length; and a second side generally opposite the first side and having a second length;
forming a second ceramic core having a length generally greater than or equal

Assignees

• United Technologies Corp

Inventors

• Propheter-Hinckley Tracy A
• Quach San
• Devore Matthew A

Classifications

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/186

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

• F05D2260/202

  by film cooling · CPC title

• B22C9/103

  Multipart cores · CPC title