Combustor panel standoffs with cooling holes

Patent metadata

Field	Value
Publication number	US-10731562-B2
Application number	US-201715651297-A
Country	US
Kind code	B2
Filing date	Jul 17, 2017
Priority date	Jul 17, 2017
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A combustor panel may comprise a panel wall comprising a proximal surface and a distal surface. A standoff may be formed over the distal surface of the panel wall. An aperture may be formed through the standoff and may extend from a face of the standoff to the proximal surface of the panel wall. The face of the first standoff may be oriented at an angle between 90 degrees and 160 degrees relative to a plane parallel to the distal surface of the panel wall.

First claim

What is claimed is:

1. A combustor panel, comprising: a panel wall comprising a proximal surface and a distal surface opposite the proximal surface; a first standoff formed over the distal surface of the panel wall, the first standoff being defined by a wall and a first face; and a first aperture formed through the first standoff and extending from the first face of the first standoff to the proximal surface of the panel wall, wherein the first aperture is cylindrically shaped, and wherein the first face of the first standoff is oriented at an angle between 90 degrees and 160 degrees relative to a plane parallel to the distal surface of the panel wall, and wherein a proximal edge of the first face is raised with respect to the distal surface, the proximal edge of the first face including a proximal point on the first face, the proximal point being a point on the first face that is located closest to the distal surface, and wherein the proximal point is located 180 degrees about a central axis of the first aperture from a distal point on the first face, the distal point on the first face being a crest point on the first face that is located farthest from the distal surface, and wherein the distal surface and a portion of the wall extending from the distal surface to the proximal point on the first face define a cavity devoid of material.

2. The combustor panel of claim 1 , wherein the central axis of the first aperture is oriented at an angle between 10 degrees and 70 degrees relative to the plane parallel to the distal surface of the panel wall.

3. The combustor panel of claim 1 , further comprising a plurality of apertures formed through the first standoff, the plurality of apertures including the first aperture.

4. The combustor panel of claim 1 , wherein the portion of the wall extending from the distal surface to the proximal edge of the first face and the distal surface of the panel wall form an angle between 10 degrees and 60 degrees.

5. The combustor panel of claim 1 , further comprising a second standoff formed over the distal surface of the panel wall, wherein a proximal edge of a second face of the second standoff is raised relative to the distal surface of the panel wall.

6. The combustor panel of claim 1 , wherein the wall of the first standoff comprises a substantially uniform thickness.

7. The combustor panel of claim 1 , wherein the first face of the first standoff comprises a circular shape.

8. The combustor panel of claim 1 , wherein a first diameter of the first aperture proximate the first face of the first standoff is less than a second diameter of the first aperture proximate the proximal surface of the panel wall.

9. A gas turbine engine, comprising: a compressor; and a combustor in fluid communication with the compressor and including a combustor panel, the combustor panel comprising: a panel wall comprising a proximal surface and a distal surface opposite the proximal surface; a first standoff formed over the distal surface of the panel wall, the first standoff being defined by a wall and a first face; and a first aperture formed through the first standoff and extending from the first face of the first standoff to the proximal surface of the panel wall, wherein the first aperture is cylindrically shaped, and wherein the first face of the first standoff is oriented at an angle between 90 degrees and 160 degrees relative, to a plane parallel to the distal surface of the panel wall, and wherein a proximal edge of the first face is raised with respect to the distal surface, the proximal edge of the first face including a proximal point on the first face, the proximal point being a point on the first face that is located closest to the distal surface, and wherein the proximal point is located 180 degrees about a central axis of the first aperture from a distal point on the first face, the distal point on the first face being a crest point on the first face that is located farthest from the distal surface, and wherein the distal surface and a portion of the wall extending from the distal surface to the proximal point on the first face define a cavity devoid of material.

10. The gas turbine engine of claim 9 , wherein the first aperture is oriented at an angle between 10 degrees and 70 degrees relative to the plane parallel to the distal surface of the panel wall.

11. The gas turbine engine of claim 9 , wherein a ratio of a thickness of the panel wall to a height of the first standoff is between 1:1 and 1:2, the thickness of the panel wall being measured between the distal surface and the proximal surface of the panel wall, the height of the first standoff being measured between the distal surface of the panel wall and a distal edge of the first standoff.

12. The gas turbine engine of claim 9 , further comprising a plurality of apertures formed through the first standoff and extending from the first face of the first standoff to the proximal surface of the panel wall, the plurality of apertures including the first aperture.

13. The gas turbine engine of claim 9 , wherein the first face of the first standoff comprises a semi-circular shape.

14. The gas turbine engine of claim 9 , further comprising a second standoff formed over the distal surface of the panel wall, wherein a proximal edge of a second face of the second standoff is raised with respect to the distal surface of the panel wall.

15. The gas turbine engine of claim 14 , further comprising a third standoff formed over the distal surface of the panel wall, wherein a third face of the third standoff is parallel to the distal surface of the panel wall.

16. A method of making a combustor panel, comprising, forming a panel wall comprising a proximal surface and a distal surface opposite the proximal surface; and forming a first standoff over the distal surface of the panel wall, the first standoff being defined by a wall and a first face and including a first aperture extending from the first face to the proximal surface of the panel wall, wherein the first aperture is cylindrically shaped, and wherein the first face of the first standoff is oriented at a first angle between 90 degrees and 160 degrees relative to a plane parallel to the distal surface of the panel wall, and wherein a proximal edge of the first face is raised with respect to the distal surface, the proximal edge of the first face including a proximal point on the first face, the proximal point being a point on the first face that is located closest to the distal surface, and wherein the proximal point is located 180 degrees about a central axis of the first aperture from a distal point on the first face, the distal point on the first face being a crest point on the first face that is located farthest front the distal surface, and wherein the distal surface and a portion of the wall extending from the distal surface to the proximal point on the first face define a cavity devoid of material.

17. The method of claim 16 , further comprising forming the first standoff using additive manufacturing.

18. The method of claim 17 , wherein the forming the first standoff comprises forming the wall of the first standoff at second angle between 10 degrees and 80 degrees relative to the distal surface of the panel wall.

19. The method of claim 16 , further comprising forming a second standoff over the distal surface of the panel wall, wherein a second face of the second standoff is oriented at a second angle relative to the plane parallel to the distal surface, and wherein the second angle is different from the first angle.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Porter Steven D
• Lemoine Jonathan

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F23R3/005 Primary

  Combined with pressure or heat exchangers · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title