Forming lined cooling aperture(s) in a turbine engine component

Patent metadata

Field	Value
Publication number	US-11913358-B2
Application number	US-202318120843-A
Country	US
Kind code	B2
Filing date	Mar 13, 2023
Priority date	Aug 13, 2021
Publication date	Feb 27, 2024
Grant date	Feb 27, 2024

Abstract

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

First claim

What is claimed is:

1. A component for a turbine engine, comprising:
a substrate comprising metal;
an external coating over the metal substrate, the external coating comprising ceramic;
a plurality of cooling apertures, a first of the plurality of cooling apertures including a meter section and a diffuser section, the meter section formed in the substrate, and the diffuser section formed in the substrate and the external coating; and
an internal coating at least partially lining the first of the plurality of cooling apertures within the substrate;
wherein the component is configured as an airfoil or a flowpath wall for the turbine engine.

2. The component of claim 1 , wherein the internal coating comprises an aluminide coating.

3. The component of claim 1 , wherein the diffuser section is configured as a multi-lobed diffuser section.

4. The component of claim 1 , wherein the external coating comprises ceramic.

5. The component of claim 1 , further comprising:
a bond coating applied on the metal substrate;
the external coating applied onto the bond coating; and
the diffuser section formed through the bond coating.

6. The component of claim 5 , wherein
the bond coating comprises MCrAlY;
the M comprises at least one of nickel (Ni), cobalt (Co) or iron (Fe); and
the Y or the X comprises at least one of hafnium (Hf), yttrium (Y) or silicon (Si).

7. The component of claim 5 , wherein
the bond coating comprises MAlCrX;
the M comprises at least one of nickel (Ni), cobalt (Co) or iron (Fe); and
the Y or the X comprises at least one of hafnium (Hf), yttrium (Y) or silicon (Si).

8. The component of claim 1 , further comprising:
a bond coating applied onto at least a portion of the internal coating;
the external coating applied onto the bond coating; and
the diffuser section formed through the bond coating.

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

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

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

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

Classifications

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• B23K26/386

  of blind holes · CPC title

• B23K26/389

  of fluid openings, e.g. nozzles, jets · CPC title

• C23C4/01

  Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated · CPC title

• C23C14/024

  Deposition of sublayers, e.g. to promote adhesion of the coating (C23C14/027 takes precedence) · CPC title