Turbine airfoil having film cooling hole arrangement

Patent metadata

Field	Value
Publication number	US-11041390-B1
Application number	US-201916690219-A
Country	US
Kind code	B1
Filing date	Nov 21, 2019
Priority date	Feb 1, 2019
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

A turbine airfoil includes a body that has inner and outer platforms and an airfoil section that extends between the inner and outer platforms. There are film cooling holes that define external breakout points from the body. The external breakout points are located in accordance with Cartesian coordinates of at least points 222 through 256 set forth in Table 1 herein.

First claim

What is claimed is:

1. A turbine airfoil comprising:
a body having inner and outer platforms and an airfoil section extending between the inner and outer platforms; and
film cooling holes that define external breakout points from the body, the external breakout points being located in accordance with Cartesian coordinates of at least points 222 through 256 set forth in Table 1.

2. The turbine airfoil as recited in claim 1 , wherein the film cooling holes having external breakout points in accordance with Cartesian coordinates of points 215 through 221 set forth in Table 1.

3. The turbine airfoil as recited in claim 2 , wherein the film cooling holes having external breakout points in accordance with Cartesian coordinates of points 1 through 215 and points 257 through 271 set forth in Table 1.

4. The turbine airfoil segment as recited in claim 1 , wherein the film cooling holes comprise divergent holes.

5. A gas turbine engine comprising:
a compressor section;
a combustor; and
a turbine section, the turbine section including an array of turbine airfoils, each turbine airfoil comprising:
a body having inner and outer platforms and an airfoil section extending between the inner and outer platforms, and
film cooling holes that define external breakout points from the body, the external breakout points being located in accordance with Cartesian coordinates of at least points 222 through 256 set forth in Table 1.

6. The gas turbine engine as recited in claim 5 , wherein the film cooling holes having external breakout points in accordance with Cartesian coordinates of points 215 through 221 set forth in Table 1.

7. The gas turbine engine as recited in claim 6 , wherein the film cooling holes having external breakout points in accordance with Cartesian coordinates of points 1 through 215 and points 257 through 271 set forth in Table 1.

8. The gas turbine engine as recited in claim 5 , wherein the film cooling holes comprise divergent holes.

9. A turbine airfoil comprising:
a body having inner and outer platforms and an airfoil section extending between the inner and outer platforms; and
film cooling holes that define external breakout points from the body, the external breakout points being located in accordance with Cartesian coordinates set forth in Table 1.

10. The turbine airfoil as recited in claim 9 , wherein the film cooling holes comprise divergent holes.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Cosher Christopher
• Arisi Allan N
• Teller Bret M
• Mentz Karl A

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F01D5/186 Primary

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