Closure element with extensions for internal passage of component

Patent metadata

Field	Value
Publication number	US-11377962-B2
Application number	US-201916561730-A
Country	US
Kind code	B2
Filing date	Sep 5, 2019
Priority date	Sep 5, 2019
Publication date	Jul 5, 2022
Grant date	Jul 5, 2022

Abstract

A closure element for an internal passage in a component, and a related method and turbine blade or nozzle are disclosed. The closure element includes a spherical body made of a first superalloy, and a plurality of extensions extending from a surface of the spherical body. The plurality of extensions made of the same, similar or different material other than the first superalloy. Subjecting the component to at least one thermal cycle causes a braze material to form a metallurgical bond with the spherical body, the plurality of extensions and the passage wall to seal the internal passage.

First claim

What is claimed is:

1. A closure element for an internal passage in a component, the closure element comprising:
a spherical body, the spherical body made of a first superalloy; and
a plurality of extensions extending from a surface of the spherical body, the plurality of extensions made of a material other than the first superalloy and bonded to the spherical body before the closure element is received in the internal passage,
wherein the plurality of extensions each has a shape of a sphere, a cone or a round plate.

2. The closure element of claim 1 , wherein the first superalloy is selected from the group comprising: a nickel-based superalloy, and a cobalt-based superalloy, and an iron-based superalloy;
wherein the plurality of extensions includes a second superalloy selected from the group comprising: a nickel-based superalloy, a cobalt-based superalloy, and an iron-based superalloy;
wherein the first superalloy is different than the second superalloy.

3. The closure element of claim 1 , further comprising a braze material disposed about the spherical body and the plurality of extensions.

4. The closure element of claim 1 , wherein the spherical body has a diameter in a range of 3 millimeters to 10 millimeters, and each extension has a dimension radially extending from the surface of the spherical body in a range of 0.3 millimeters to 5 millimeters, wherein the dimension of each extension is smaller than the diameter of the spherical body.

5. The closure element of claim 1 , wherein the spherical body with the plurality of extensions are collectively sized and shaped to be received against at least one internal passage wall in an interference fit proximate a closure site of the internal passage.

6. A closure element for an internal passage in a component, the closure element comprising:
a spherical body, the spherical body made of a first superalloy; and
a plurality of extensions extending from a surface of the spherical body, the plurality of extensions made of a material other than the first superalloy, wherein the plurality of extensions includes uniformly distributed extensions.

7. The closure element of claim 6 , wherein the uniformly distributed extensions include six uniformly distributed extensions.

8. The closure element of claim 6 , wherein the plurality of extensions are symmetrically distributed about the spherical body.

9. A method, comprising:
inserting a closure element into an internal passage of a component, the closure element including a spherical body and a plurality of extensions extending from a surface of the spherical body, wherein at least one of the plurality of extensions engages with a passage wall of the internal passage to position the spherical body at a closure site;
applying a braze material at the closure site; and
subjecting the component to at least one thermal cycle such that the braze material forms a metallurgical bond with the spherical body, the plurality of extensions and the passage wall to seal the internal passage,
wherein the plurality of extensions were bonded to the spherical body before the closure element is inserted into the internal passage, and
wherein the plurality of extensions each has a shape of: a sphere, a cone or a round plate.

10. The method of claim 9 , further comprising forming the closure element by attaching the plurality of extensions to a surface of the spherical body, the spherical body having a diameter incapable of seating in the closure site of the internal passage in the component.

11. The method of claim 10 , wherein attaching the plurality of extensions includes tack welding the plurality of extensions to the surface of the spherical body.

12. The method of claim 10 , wherein attaching the plurality of extensions includes fusion welding the plurality of extensions to the surface of the spherical body.

13. The method of claim 9 , further comprising, prior to the inserting:
applying an anti-oxidation layer over the passage wall of the internal passage; and
removing the anti-oxidation layer at the closure site.

14. The method of claim 9 , wherein the spherical body has a diameter in a range of 3 millimeters to 10 millimeters, and each extension has a dimension radially extending from the surface of the spherical body in a range of 0.3 millimeters to 5 millimeters, wherein the dimension of each extension is smaller than the diameter of the spherical body.

15. The method of claim 14 , wherein the spherical body includes a first superalloy selected from the group comprising: a nickel-based superalloy, a cobalt-based superalloy and an iron-based superalloy;
wherein the plurality of extensions include a second superalloy selected from the group comprising: a nickel-based superalloy, a cobalt-based superalloy, and an iron-based superalloy;
wherein the first superalloy is different than the second superalloy.

16. The method of claim 13 , wherein the spherical body with the plurality of extensions are collectively sized and shaped to be received against the passage wall in an interference fit proximate the closure site of the internal passage.

17. A turbine blade or nozzle, comprising:
a body;
an internal passage in the body, the internal passage including a passage wall;
a closure element at a closure site in the internal passage, the closure element including a spherical body, and a plurality of extensions in a surface of the spherical body, the spherical body and the plurality of extensions forming a metallurgical bond with the passage wall to seal the internal passage,
wherein the plurality of extensions were bonded to the spherical body before the closure element is received in the internal passage, and
wherein the plurality of extensions each has a shape of: a sphere, a cone or a round plate.

18. The turbine blade or nozzle of claim 17 , wherein the spherical body includes a first superalloy selected from the group comprising: a nickel-based superalloy, a cobalt-based superalloy, and an iron-based superalloy;
wherein the plurality of extensions include a second superalloy selected from the group comprising: a nickel-based superalloy, a cobalt-based superalloy, and an iron-based superalloy; and
wherein the first superalloy is different than the second superalloy.

19. The turbine blade or nozzle of claim 17 , wherein the plurality of extensions include uniformly distributed extensions.

Assignees

• Gen Electric

Inventors

• Cui Yan
• Arnett Michael Douglas
• Laylock Matthew Joseph
• Tollison Brian Lee

Classifications

• B23K1/0018

  Brazing of turbine parts · CPC title

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• C22C19/00

  Alloys based on nickel or cobalt · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title