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

Patent metadata

Field	Value
Publication number	US-10830052-B2
Application number	US-201615266481-A
Country	US
Kind code	B2
Filing date	Sep 15, 2016
Priority date	Sep 15, 2016
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

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 method of manufacturing a cooled gas turbine component for a gas turbine engine, the method comprising:
forming a core with an outer surface, the outer surface including a core feature that projects from the core;
casting an outer wall of an airfoil about the core including casting a portion of the outer wall that covers the core feature and projecting the core feature partially into a thickness of the outer wall, the portion including an exterior surface and an interior surface, the interior surface defining a shaped inlet portion that is cast to inversely correspond to the core feature; and
after casting the outer wall, forming an outlet portion through the outer wall by progressively removing material through the portion of the outer wall in a direction from the exterior surface toward the interior surface and toward the shaped inlet portion to fluidly connect the outlet portion to the shaped inlet portion, the shaped inlet portion and the outlet portion cooperatively defining a cooling aperture through the outer wall.

2. The method of claim 1 , further comprising adjusting the outlet portion by changing a dimension of the outlet portion.

3. The method of manufacturing of claim 1 ,
wherein forming the core includes forming the core feature to be at least partially conic.

4. The method of manufacturing of claim 1 , wherein forming the outlet portion includes extending the outlet portion along an axis;
wherein the axis extends at an acute angle relative to the exterior surface of the outer wall.

5. The method of claim 1 , wherein forming the outlet portion includes forming the outlet portion to have a substantially constant width along a length of the outlet portion.

6. The method of claim 1 , wherein forming the outlet portion includes extending the aperture through the shaped inlet portion, leaving at least part of the shaped inlet portion continuously encompassing the outlet portion.

7. The method of claim 1 , wherein forming the core includes molding the core within a die.

8. The method of claim 1 , wherein forming the core includes forming a recess on the outer surface of the core; and
wherein forming the core includes forming the core feature as a projection that is disposed in the recess.

9. The method of claim 1 , wherein a depth of the inlet portion is, at most, one third of a length of the cooling aperture.

10. The method of claim 1 , wherein the inlet portion comprises a chamfer of the outlet portion.

11. The method of claim 1 , wherein casting the outer wall includes forming the shaped inlet portion to have a convex curvature.

12. The method of claim 1 , wherein casting the outer wall includes forming the shaped inlet portion to have a width that varies.

13. A method of manufacturing a cooled gas turbine component for a gas turbine engine, the method comprising:
forming a core with an outer surface, the outer surface including a core feature;
casting an outer wall of an airfoil about the core including casting a portion of the outer wall that covers the core feature, the portion including an exterior surface and an interior surface, the interior surface defining a shaped inlet portion that is cast to inversely correspond to the core feature;
after casting the outer wall, forming an outlet portion through the outer wall by progressively removing material through the portion of the outer wall in a direction from the exterior surface toward the interior surface and toward the shaped inlet portion to fluidly connect the outlet portion to the shaped inlet portion, the shaped inlet portion and the outlet portion cooperatively defining a cooling aperture through the outer wall;
re-casting the outer wall; and
forming an adjusted outlet portion through the re-cast outer wall.

14. The method of claim 13 , wherein forming the outlet portion through the outer wall includes forming the outlet portion at a first axis relative to the exterior surface of the outer wall;
wherein forming the adjusted outlet portion through the re-cast outer wall includes forming the adjusted outlet portion at a second axis relative to an exterior surface of the re-cast outer wall; and
wherein the second axis is disposed at an angle relative to the first axis.

15. A method of manufacturing a cooled gas turbine component for a gas turbine engine, the method comprising:
forming a core with an outer surface, the outer surface including a core feature that projects from the core;
casting an outer wall of an airfoil about the core including casting a portion of the outer wall that covers the core feature, the portion including an exterior surface and an interior surface, the interior surface defining a shaped inlet portion that is cast to inversely correspond to the core feature; and
after casting the outer wall, forming an outlet portion through the outer wall by progressively removing material through the portion of the outer wall in a direction from the exterior surface toward the interior surface and toward the shaped inlet portion to fluidly connect the outlet portion to the shaped inlet portion, the shaped inlet portion and the outlet portion cooperatively defining a cooling aperture through the outer wall, the shaped inlet portion having a first width that varies, the outlet portion having a second width that is substantially constant.

16. The method of claim 15 , wherein forming the core includes forming the core feature to be at least partially conic.

17. The method of claim 15 , wherein forming the outlet portion includes extending the aperture through the shaped inlet portion, leaving at least part of the shaped inlet portion continuously encompassing the outlet portion.

18. The method of claim 15 , wherein a depth of the inlet portion is, at most, one third of a length of the cooling aperture.

19. The method of claim 15 , wherein the inlet portion comprises a chamfer of the outlet portion.

20. The method of claim 15 , wherein casting the outer wall includes forming the shaped inlet portion to have a convex curvature.

Assignees

• Honeywell Int Inc

Inventors

• Howe Jeff
• Tapia Luis

Classifications

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D5/186 Primary

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

• B22C7/02

  Lost patterns · CPC title

• B22C9/04

  Use of lost patterns · CPC title

• B22C9/10

  Cores; Manufacture or installation of cores {(breaker cores B22C9/084)} · CPC title