Methods for forming cooling apertures in a turbine engine component

Patent metadata

Field	Value
Publication number	US-11813706-B2
Application number	US-202117401947-A
Country	US
Kind code	B2
Filing date	Aug 13, 2021
Priority date	Aug 13, 2021
Publication date	Nov 14, 2023
Grant date	Nov 14, 2023

Abstract

A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate. An outer coating is applied over the substrate. A characteristic of the outer coating is determined. Instructions for forming a cooling aperture are revised based on the characteristic of the outer coating to provide revised instructions. The cooling aperture is formed in the outer coating and the substrate based on the revised instructions.

First claim

What is claimed is:

1. A manufacturing method, comprising:
providing a preform component for a turbine engine, the preform component comprising a substrate;
providing instructions for forming a cooling aperture;
applying an outer coating over the substrate;
determining a characteristic of the outer coating;
revising the instructions for forming the cooling aperture based on the characteristic of the outer coating to provide revised instructions; and
forming the cooling aperture in the outer coating and the substrate based on the revised instructions, the cooling aperture including a diffuser section and a meter section, the diffuser section formed during the forming of the cooling aperture at least in the outer coating, and the meter section formed during the forming of the cooling aperture in the substrate.

2. The manufacturing method of claim 1 , wherein the characteristic of the outer coating comprises a thickness of the outer coating.

3. The manufacturing method of claim 1 , wherein the characteristic of the outer coating comprises a surface topology of the outer coating.

4. The manufacturing method of claim 1 , wherein
the instructions specify a dimension of the diffuser section to have a first value; and
the revised instructions specify the dimension of the diffuser section to have a second value that is different than the first value.

5. The manufacturing method of claim 1 , wherein
the instructions specify a dimension of the meter section to have a first value; and
the revised instructions specify the dimension of the meter section to have a second value that is different than the first value.

6. The manufacturing method of claim 1 , wherein at least a portion of the diffuser section and at least a portion of the meter section are formed using a common machining process.

7. The manufacturing method of claim 1 , wherein
at least a portion of the diffuser section is formed using a first machining process; and
at least a portion of the meter section is formed using a second machining process that is different than the first machining process.

8. The manufacturing method of claim 1 , wherein the characteristic of the outer coating is determined using artificial intelligence.

9. The manufacturing method of claim 1 , wherein the characteristic of the outer coating is determined using machine learning.

10. The manufacturing method of claim 1 , further comprising:
scanning the substrate using an imaging system to provide substrate data prior to the applying of the outer coating; and
scanning the outer coating using the imaging system to provide outer coating data;
wherein the determining of the characteristic of the outer coating comprises comparing the coating data with the substrate data.

11. The manufacturing method of claim 1 , wherein the determining of the characteristic of the outer coating comprises scanning the outer coating with an imaging system to determine an internal structural feature of the outer coating.

12. The manufacturing method of claim 1 , wherein the preform component comprises a preform of an airfoil for the turbine engine.

13. The manufacturing method of claim 1 , wherein the preform component comprises a preform of a flowpath wall for the turbine engine.

14. A manufacturing method, comprising:
providing a preform component for a turbine engine, the preform component comprising a substrate;
providing a design specification for a cooling aperture;
applying an outer coating over the substrate;
adapting the design specification for the cooling aperture based on a characteristic of the outer coating to provide an adapted design specification; and
forming the cooling aperture in the outer coating and the substrate based on the adapted design specification, wherein a meter section of the cooling aperture is formed in the substrate after the outer coating is applied over the substrate.

15. The manufacturing method of claim 14 , wherein the adapting of the design specification changes a value of a dimension for the cooling aperture.

16. The manufacturing method of claim 14 , wherein the adapting of the design specification changes a geometry of the cooling aperture.

17. The manufacturing method of claim 14 , wherein the adapting of the design specification changes a spatial orientation of the cooling aperture.

18. The manufacturing method of claim 14 , further comprising determining the characteristic of the outer coating using at least one of artificial intelligence, machine learning or an imaging system.

19. A manufacturing method, comprising:
providing a preform component for a turbine engine, the preform component comprising a substrate;
providing instructions for forming a diffuser section of a cooling aperture;
applying an outer coating over the substrate;
determining a thickness of the outer coating applied over the substrate;
adapting the instructions for forming the diffuser section of a cooling aperture based on the thickness of the outer coating to provide revised instructions; and
forming an entirety of the cooling aperture in at least the substrate and the outer coating after the outer coating is applied over the substrate, the forming of the cooling aperture comprising forming the diffuser section of the cooling aperture at least in the outer coating based on the revised instructions.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Craig Brian
• Koonankeil James M
• Hazel Brian T
• Denney Paul E
• Mongillo Dominic J

Classifications

• B23P15/00 Primary

  Making specific metal objects by operations not covered by a single other subclass or a group in this subclass · CPC title

• B23P2700/06

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

• F05D2220/30

  in turbines · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title