Cupped contour for gas turbine engine blade assembly

Patent metadata

Field	Value
Publication number	US-10344597-B2
Application number	US-201514828063-A
Country	US
Kind code	B2
Filing date	Aug 17, 2015
Priority date	Aug 17, 2015
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

An exemplary method of forming an endwall with a contour includes casting an endwall with at least one cooling channel having an opening from the endwall, and covering the opening with a cupped contour formed on the endwall. An exemplary gas turbine engine blade assembly includes an endwall with a plurality of cooling channels, an airfoil extending radially from the endwall to a tip, and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.

First claim

What is claimed is:

1. A method of forming an endwall with a contour, comprising:
casting the endwall with at least one cooling channel having an opening from the endwall, wherein an airfoil extends in a radial direction from the endwall to a tip;
covering the opening with a cupped contour that is formed on the endwall to provide a portion of a gas path surface, including defining the cooling chamber between the cupped contour and an external surface of the endwall;
forming the cupped contour on a radially facing surface of the endwall with respect to the radial direction; and
forming a groove along the external surface of the endwall such that a length of the groove defines the opening along the radially facing surface.

2. The method of claim 1 , further comprising forming the cupped contour on the endwall using additive manufacturing.

3. The method of claim 1 , wherein the endwall has a first material composition, and the cupped contour has a second material composition different than the first material composition.

4. The method of claim 1 , further comprising covering an inlet to at least one cooling channel of the endwall with the cupped contour.

5. The method of claim 4 , wherein an outlet and the inlet open to the cooling chamber provided by the cupped contour.

6. The method of claim 5 , wherein the endwall is an endwall of a blade.

7. The method of claim 6 , further comprising forming the cupped contour on the endwall using additive manufacturing.

8. The method of claim 7 , further comprising:
providing the at least one cooling channel in the endwall using a core held within a mold during the casting;
wherein a portion of the core providing the opening of the at least one cooling channel provides an attachment point that secures the core within the mold; and
wherein the endwall is an endwall of a blade assembly and the attachment point is a first attachment point, wherein a second attachment point that secures the core within the mold is adjacent a blade tip of the blade assembly, and a third attachment point that secures the core within the mold is adjacent a root of the blade assembly.

9. The method of claim 8 , wherein the endwall has a first material composition, and the cupped contour has a second material composition different than the first material composition.

10. The method of claim 5 , wherein:
the at least one cooling channel include a plurality of cooling channels, and the opening of each of the plurality of cooling channels in communication with the cooling chamber.

11. The method of claim 10 , wherein the endwall is an endwall of a turbine blade.

12. The method of claim 1 , wherein the endwall is an endwall of a blade.

13. The method of claim 1 , further comprising providing the at least one cooling channel in the endwall using a core held within a mold during the casting.

14. The method of claim 13 , wherein a portion of the core providing the opening of the at least one cooling channel provides an attachment point that secures the core within the mold.

15. The method of claim 14 , wherein the endwall is an endwall of a blade assembly and the attachment point is a first attachment point, wherein a second attachment point that secures the core within the mold is adjacent a blade tip of the blade assembly, and a third attachment point that secures the core within the mold is adjacent a root of the blade assembly.

16. A method of forming an endwall with a contour comprising:
covering an inlet to at least one cooling channel of the endwall with the cupped contour;
wherein an outlet and the inlet open to a cooling chamber provided by the cupped contour;
wherein the step of covering the opening includes defining the cooling chamber between the cupped contour and an external surface of the endwall;
wherein the at least one cooling channel include a plurality of cooling channels, and the opening of each of the plurality of cooling channels in communication with the cooling chamber; and
forming a groove along the external surface of the endwall such that a length of the groove defines the opening.

17. The method of claim 16 , wherein:
an airfoil extends in a radial direction from the endwall to a tip; and
the cooling chamber is defined between the cupped contour and a radially facing surface of the endwall with respect to the radial direction, the external surface being the radially facing surface.

18. The method of claim 17 , wherein:
the inlet communicates flow from the cooling chamber; and
the outlet communicates flow to the cooling chamber.

19. The method of claim 18 , wherein the cooling chamber is radially outside the external surface of the endwall such that the endwall is entirely radially misaligned from the cooling chamber with respect to the radial direction.

Assignees

• United Technologies Corp

Inventors

• Saha Dipanjan
• Snyder Brooks E
• Slavens Thomas N

Classifications

• B22F10/20

  Direct sintering or melting · CPC title

• B22F10/64

  by thermal means (control of energy beam parameters for post heating B22F10/364) · CPC title

• F05D2230/21

  by casting · CPC title

• B23K2101/001

  Turbines · CPC title

• F05D2260/204

  by the use of microcircuits · CPC title