Gas turbine component with cooling aperture having shaped inlet and method of forming the same

Patent metadata

Field	Value
Publication number	US-11208900-B2
Application number	US-201916555696-A
Country	US
Kind code	B2
Filing date	Aug 29, 2019
Priority date	Sep 15, 2016
Publication date	Dec 28, 2021
Grant date	Dec 28, 2021

Abstract

A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.

First claim

What is claimed is:

1. A cooled gas turbine component for a gas turbine engine comprising:
an airfoil;
a cast outer wall of the airfoil, the outer wall having an exterior surface and an interior surface, the outer wall having a thickness measured between the exterior surface and the interior surface, the outer wall including a constant-thickness portion at which the thickness is constant; and
a cooling aperture that extends along an axis through the constant-thickness portion of the outer wall, the cooling aperture having a length measured along the axis, the cooling aperture being a partly-cast aperture along the length and being a partially-machined aperture along the length, the cooling aperture including:
a cast inlet portion included on and recessed relative to the interior surface; and
a machined outlet portion that is straight and linear along the axis, that is fluidly connected to the inlet portion at an intersection, and that extends through the outer wall to the exterior surface, the outlet portion having a diameter that remains constant from the exterior surface to the intersection;
wherein the inlet portion has a width and a depth, wherein the width of the inlet portion gradually reduces along the depth of the inlet portion toward the outlet portion; and
wherein the inlet width of the inlet portion at the intersection is greater than the diameter at the intersection to define a step at the intersection.

2. The cooled gas turbine component of claim 1 ,
wherein the inlet portion is at least partially conic.

3. The cooled gas turbine component of claim 1 , wherein the axis of the outlet portion extends at an acute angle relative to the exterior surface of the outer wall.

4. The cooled gas turbine component of claim 3 , wherein the acute angle is, at most, seventy-eight degrees (78°).

5. The cooled gas turbine component of claim 3 , wherein the airfoil includes a leading edge and a trailing edge, and wherein the axis of the outlet portion extends at the acute angle to direct the outlet portion toward the trailing edge of the airfoil.

6. The cooled gas turbine component of claim 1 , wherein the inlet portion continuously surrounds the outlet portion about the axis to widen the cooling aperture about an entire periphery thereof at the interior surface.

7. The cooled gas turbine component of claim 1 , wherein the depth of the inlet portion is, at most, one third of the length of the cooling aperture.

8. The cooled gas turbine component of claim 1 , wherein the inlet portion defines a chamfer that extends to the outlet portion.

9. The cooled gas turbine component of claim 1 , wherein a surface of the inlet portion has a convex curvature.

10. The cooled gas turbine component of claim 1 , further comprising an internal wall that separates a first cavity from a second cavity within the airfoil;
further comprising an internal channel that extends through the internal wall and that fluidly connects the first cavity and the second cavity; and
wherein a first width of the cooling aperture is smaller than a second width of the internal channel.

11. A cooled gas turbine component for a gas turbine engine comprising:
an airfoil;
an outer wall of the airfoil, the outer wall having an exterior surface and an interior surface, the outer wall having a thickness measured between the exterior surface and the interior surface, the outer wall including a constant-thickness portion at which the thickness is constant; and
a cooling aperture that extends along an axis through the constant-thickness portion of the outer wall, the cooling aperture including:
a shaped inlet portion included on and recessed relative to the interior surface; and
an outlet portion having an outlet axis that is straight and linear, extending through the outer wall, and fluidly connected to the inlet portion at an intersection, the outlet portion having a diameter that remains constant from the exterior surface to the intersection;
wherein the inlet portion continuously surrounds the outlet portion about the axis to widen the cooling aperture about an entire periphery thereof at the interior surface, the inlet portion having an inlet width and a depth, wherein the inlet width of the inlet portion tapers and reduces along the depth of the inlet portion and fluidly connects to the outlet portion at the intersection; and
wherein the inlet width of the inlet portion at the intersection is greater than the diameter at the intersection to define a step at the intersection.

12. The cooled gas turbine component of claim 11 , wherein the inlet portion is frusto-conic.

13. The cooled gas turbine component of claim 11 ,
wherein the outlet axis extends at an acute angle relative to the exterior surface of the outer wall.

14. The cooled gas turbine component of claim 13 , wherein the airfoil includes a leading edge and a trailing edge, and wherein the outlet axis extends at the acute angle to direct the outlet portion toward the trailing edge of the airfoil.

15. The cooled gas turbine component of claim 11 , wherein the depth of the inlet portion is, at most, one third of a length of the cooling aperture.

16. The cooled gas turbine component of claim 11 , wherein a surface of the inlet portion has a convex curvature.

17. The cooled gas turbine component of claim 11 , wherein the shaped inlet portion has an inlet surface with a cast surface finish; and
wherein the outlet portion has an outlet surface with a machined surface finish.

Assignees

• Honeywell Int Inc

Inventors

• Howe Jeff
• Tapia Luis

Classifications

• Y02T50/60

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

• F05D2230/21

  by casting · CPC title

• F02K3/06

  with front fan · CPC title

• B22C9/04

  Use of lost patterns · CPC title

• F05D2260/202

  by film cooling · CPC title