Forming and/or inspecting cooling aperture(s) in a turbine engine component

Patent metadata

Field	Value
Publication number	US-2025052695-A1
Application number	US-202418921719-A
Country	US
Kind code	A1
Filing date	Oct 21, 2024
Priority date	Aug 13, 2021
Publication date	Feb 13, 2025
Grant date	—

Abstract

A manufacturing method is provided. During this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.

First claim

What is claimed is:

1 . A method involving an imaging system, comprising:
providing a component for a turbine engine, the component including a substrate, an external coating over the substrate, a meter section of a cooling aperture formed in the substrate and a diffuser section of the cooling aperture formed in the external coating and the substrate; scanning at least a portion of the component using the imaging system to provide scan data indicative of an internal structure of the portion of the component, wherein the portion of the component includes the meter section; and performing an operation based on the scan data, the operation comprising evaluating an alignment between the diffuser section and the meter section based on the scan data.

2 . The method of claim 1 , wherein the imaging system comprises a microwave imaging system.

3 . The method of claim 1 , wherein the providing of the component comprises forming the meter section in the substrate;
applying the external coating over the substrate; and forming the diffuser section in the external coating and the substrate.

4 . The method of claim 3 , wherein the providing of the component further comprises applying an internal coating onto a surface of the meter section prior to applying the external coating onto the substrate.

5 . The method of claim 4 , wherein the internal coating comprises an aluminide coating.

6 . The method of claim 4 , wherein the internal coating comprises PtAl.

7 . The method of claim 4 , wherein the internal coating comprises NiCoCrAlY.

8 . The method of claim 3 , wherein the providing of the component comprises applying a bond coating onto the substrate prior to applying the external coating onto the substrate, wherein the external coating is applied onto the bond coating, and the diffuser section is further formed through the bond coating.

9 . The method of claim 3 , wherein the meter section is formed in the substrate using an electric discharge machining process.

10 . The method of claim 3 , wherein the diffuser section is formed in the external coating and the substrate using a laser machining process.

11 . The method of claim 1 , wherein the substrate comprises metal.

12 . The method of claim 1 , wherein the external coating comprises ceramic.

13 . The method of claim 1 , wherein the component comprises an airfoil for the turbine engine.

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

15 . An inspection method, comprising:
providing a component of a turbine engine, the component comprising a plurality of cooling apertures, a first of the plurality of cooling apertures including a diffuser section and a meter section; scanning at least a portion of the component with an imaging system to provide scan data indicative of an internal structure of the portion of the component; and processing the scan data to evaluate alignment between the diffuser section and the meter section.

16 . The inspection method of claim 15 , further comprising indicating alignment of the diffuser section and the meter section where a centerline of the diffuser section is coincident with a centerline of the meter section at an interface between the diffuser section and the meter section.

17 . The inspection method of claim 15 , further comprising indicating alignment of the diffuser section and the meter section where a lateral offset between the diffuser section and the meter section is less than a threshold.

18 . The inspection method of claim 15 , further comprising indicating misalignment of the diffuser section and the meter section where a lateral offset between the diffuser section and the meter section is greater than a threshold.

19 . The inspection method of claim 15 , wherein the imaging system comprises a microwave imaging system.

20 . The inspection method of claim 15 , wherein the component comprises a metal substrate a ceramic external coating, and the first of the plurality of cooling apertures is formed in the metal substrate and the ceramic external coating.

Assignees

• Rtx Corp

Inventors

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

Classifications

• C23C28/34

  including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F05D2250/324

  divergent · CPC title