Staggered core printout

Patent metadata

Field	Value
Publication number	US-9988910-B2
Application number	US-201514609677-A
Country	US
Kind code	B2
Filing date	Jan 30, 2015
Priority date	Jan 30, 2015
Publication date	Jun 5, 2018
Grant date	Jun 5, 2018

Abstract

A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body. The plurality of core extensions are positioned to be staggered relative to each other such that at least two adjacent core extensions are variable relative to each other in at least one dimension. A gas turbine engine component is also disclosed.

First claim

The invention claimed is:

1. A gas turbine engine component comprising:
a body extending between first and second ends to define a length and extending between first and second edges to define a width;
a plurality of openings formed within a wall surface of the body, wherein the plurality of openings are positioned to be staggered relative to each other such that at least two adjacent openings are offset from each other in at least one direction; and
an arc segment formed along the length of the body, wherein the openings are spaced apart from each other along the arc segment.

2. The component according to claim 1 including a point along one of the first and second edges that defines a radius of curvature for the arc segment.

3. The component according to claim 2 wherein the body comprises an airfoil with the first edge comprising a leading edge, the second edge comprising a trailing edge, the first end comprising a radially inner portion and the second end comprising a tip portion, and wherein the point is located at a position that is nearer to the leading edge than the trailing edge.

4. The component according to claim 3 wherein flow exiting the openings is generally parallel or angled relative to an associated streamline path.

5. The component according to claim 4 wherein the body includes an internal cooling channel and a passage that leads from the internal cooling channel to an external surface of the body, and wherein the openings comprise polygonal or curved openings in the external surface.

6. The component according to claim 4 wherein the openings are formed in a pressure and/or suction side of the airfoil.

7. The component according to claim 4 wherein the openings are formed in a platform for a vane, blade, or blade outer air seal.

8. The component according to claim 1 wherein the openings are spaced apart from each other along the arc segment extending between the first and second ends.

9. The component according to claim 8 wherein the body includes an internal cooling channel and a passage that leads from the internal cooling channel to an external surface of the body, and wherein the openings comprise polygonal or curved openings in the external surface.

10. The component according to claim 1 wherein the body comprises one of an airfoil, a blade, a vane, a blade outer air seal, or a combustor panel.

11. The component according to claim 2 wherein the body comprises an airfoil with the first edge comprising a leading edge, the second edge comprising a trailing edge, the first end comprising a radially inner portion and the second end comprising a tip portion, and wherein the point is located at a position that is nearer to the trailing edge than the leading edge.

12. The component according to claim 2 wherein the body comprises an airfoil with the first edge comprising a leading edge, the second edge comprising a trailing edge, the first end comprising a radially inner portion and the second end comprising a tip portion, and wherein the point is located at a position that is nearer to a pressure side than a suction side.

13. The component according to claim 2 wherein the body comprises an airfoil with the first edge comprising a leading edge, the second edge comprising a trailing edge, the first end comprising a radially inner portion and the second end comprising a tip portion, and wherein the point is located at a position that is nearer to a suction side than a pressure side.

14. The component according to claim 2 wherein the body comprises an airfoil with the first edge comprising a leading edge, the second edge comprising a trailing edge, the first end comprising a radially inner portion and the second end comprising a tip portion, and wherein the point is located at a position that nearer to an engine centerline than the tip portion.

15. The component according to claim 1 , wherein the arc segment curves between first and second arc ends, and wherein openings at each of the first and second arc ends are closer to one of the first and second edges than remaining openings that are located between the openings at each of the first and second arc ends.

16. The component according to claim 1 , wherein the body comprises an airfoil with the first edge comprising a leading edge, the second edge comprising a trailing edge, the first end comprising a radially inner portion and the second end comprising a tip portion, and including a point along the leading edge that defines a radius of curvature for the arc segment such that openings at a center portion of the arc segment are nearer to the trailing edge than the openings at each opposing end of the arc segment.

Assignees

• United Technologies Corp

Inventors

• King Christopher

Classifications

• F01D25/12

  Cooling · CPC title

• F05D2230/21

  by casting · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2230/30

  with deposition of material · CPC title

• F01D5/186 Primary

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