Additive manufacturing method for making complex film holes

Patent metadata

Field	Value
Publication number	US-10350684-B2
Application number	US-201514937325-A
Country	US
Kind code	B2
Filing date	Nov 10, 2015
Priority date	Nov 10, 2015
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

A method of forming a cooling hole structure on a turbine component. The turbine component has a component wall with inner and outer surfaces. A bore passes through the component wall and fluidly connects the inner surface and the outer surface. The method includes the steps of: A) forming a recess communicating with the bore and the outer surface; and B) using an additive manufacturing process to form an exit region in the recess.

First claim

What is claimed is:

1. A method of forming a cooling hole structure on a turbine component, the method comprising:
forming a recess in a component wall, the wall having an inner surface and an outer surface, and a bore passing through the component wall and fluidly connecting the inner surface and the outer surface, the recess fluidly communicating with the bore and the outer surface; and
using an additive manufacturing process to form an exit region in the recess, the additive manufacturing process comprising sequentially depositing a plurality of layers of metal powder and fusing the metal powder using a directed energy source, the exit region comprising fused metal powder that at least partially refills the recess with a cooling hole therethrough fluidly communicating with the bore and the outer surface, the cooling hole defined by an inner surface of the fused metal powder.

2. The method of claim 1 further comprising depositing metal powder on a first surface that defines at least a portion of the recess; and
fusing the metal powder in a pattern corresponding to a layer of the cooling hole structure.

3. The method of claim 2 further comprising repeating in a cycle the steps of depositing and fusing to build up the cooling hole structure in a layer-by-layer fashion.

4. The method of claim 3 wherein the repeating cycle of depositing and fusing results in the component including both fused and un-fused metal powder, the method further comprising removing the un-fused metal powder.

5. The method of claim 2 wherein the metal powder is adhered to the first surface by:
applying an adhesive to the first surface; and
applying powder to the adhesive.

6. The method of claim 5 further comprising removing excess metal powder after the metal powder is applied to the adhesive.

7. The method of claim 2 further comprising forming a plug in the bore and depositing metal powder on the plug.

8. The method of claim 7 further comprising fusing the metal powder such that the pattern leaves unfused metal powder over at least a portion of the plug.

9. The method of claim 8 further comprising forming a diffusing section by fusing subsequent layers such that unfused metal powder of each subsequent layer overlaps unfused metal powder of a previous layer.

10. The method of claim 1 wherein the component comprises a metal alloy.

11. The method of claim 1 wherein the metal powder comprises a metal alloy.

12. A method of forming a film-cooling hole structure on a turbine component, the method comprising:
forming a recess in a component wall, the wall having an inner surface and an outer surface, and a bore passing through the component wall and fluidly connecting the inner surface and the outer surface, the recess fluidly communicating with the bore and the outer surface; and
using an additive manufacturing process to form a section of a film-cooling hole within the recess, the additive manufacturing process comprising sequentially depositing a plurality of layers of metal powder and fusing the metal powder using a directed energy source, the section of the film-cooling hole defined by fused metal powder that at least partially refills the recess with the film-cooling hole passing therethrough, the section of the film-cooling hole changing dimension with distance along a longitudinal centerline of the film-cooling hole.

13. The method of claim 12 further comprising depositing metal powder on a first surface that defines at least a portion of the recess; and
fusing the metal powder in a pattern corresponding to a layer of the film-cooling hole structure.

14. The method of claim 13 further comprising repeating in a cycle the steps of depositing and fusing to build up the film-cooling hole structure in a layer-by-layer fashion.

15. The method of claim 14 wherein the cycle of depositing and fusing results in the component including both fused and un-fused metal powder, the method further comprising removing the un-fused metal powder.

16. The method of claim 13 wherein the metal powder is adhered to the first surface by:
applying an adhesive to the first surface; and
applying metal powder to the adhesive.

17. The method of claim 16 further comprising removing excess metal powder after the metal powder is applied to the adhesive.

18. The method of claim 13 further comprising forming a plug in the bore and depositing metal powder in a layer that at least partially overlaps the plug.

19. The method of claim 18 further comprising fusing the metal powder in the layer such that the pattern leaves unfused metal powder over at least a portion of the plug.

20. The method of claim 19 further comprising forming an exit section of the film hole by fusing subsequent layers such that unfused metal powder of each subsequent layer overlaps both unfused and fused metal powder of a previous layer.

Assignees

• Gen Electric

Inventors

• Bunker Ronald Scott

Classifications

• B23P2700/06

  Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components · CPC title

• B22F10/68

  Cleaning or washing · CPC title

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• F05D2230/20

  essentially without removing material · CPC title