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EP-4737691-A2 - METHOD FOR INSPECTING COOLING APERTURES IN A TURBINE ENGINE COMPONENT

EP4737691A2EP 4737691 A2EP4737691 A2EP 4737691A2EP-4737691-A2

Abstract

A manufacturing method is provided. During this method, a preform component (60') for a turbine engine is provided that includes a substrate (74). A meter section (102) of a cooling aperture (64) is formed in the substrate (74'). An external coating (76',78') is applied over the substrate. At least a portion of the substrate (74') and the external coating (76',78') is scanned with an imaging system (156) to provide scan data indicative of an internal structure of the portion of the substrate (74') and the external coating (76',78'). A diffuser section of the cooling aperture is formed in the external coating (76',78') and the substrate (74') based on the scan data.

Inventors

  • CRAIG, BRIAN
  • KOONANKEIL, JAMES M.
  • HAZEL, BRIAN T.
  • DENNEY, PAUL E.
  • MONGILLO, DOMINIC J.

Assignees

  • RTX Corporation

Dates

Publication Date
20260506
Application Date
20220815

Claims (15)

  1. A method involving an imaging system, comprising: providing a component for a turbine engine (20), the component including a substrate (74) and a meter section (102) of a cooling aperture (64) formed in the substrate (74); 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 (102); and performing an operation based on the scan data.
  2. The method of claim 1, wherein the component further includes an external coating (76',78') over the substrate (74); and the operation comprises forming a diffuser section (104) of the cooling aperture (64) in the external coating (76',78') and the substrate (74) based on the scan data.
  3. The method of claims 1 or 2, wherein the component further includes an external coating (76',78') over the substrate (74) and a diffuser section (104) of the cooling aperture (64) formed in the external coating (76',78') and the substrate (74); and the operation comprises evaluating an alignment between the diffuser section (104) and the meter section (102) based on the scan data.
  4. A manufacturing method, comprising: providing a preform component (60') for a turbine engine (20), the preform component (60') comprising a substrate (74); forming a meter section (102) of a cooling aperture (64) in the substrate (74); applying an external coating (76',78') over the substrate (74); scanning at least a portion of the substrate (74) and the external coating (76',78') with an imaging system (156) to provide scan data indicative of an internal structure of the portion of the substrate (74) and the external coating (76',78'); and forming a diffuser section (104) of the cooling aperture (64) in the external coating (76',78') and the substrate (74) based on the scan data.
  5. The manufacturing method of claim 4, further comprising applying an internal coating (138) onto a surface of the meter section (102) prior to applying the external coating (76',78') onto the substrate (74).
  6. The manufacturing method of claim 5, wherein the internal coating (138) comprises one of an aluminide coating, PtAl, and NiCoCrAlY.
  7. The manufacturing method of any of claims 4 to 6, further comprising: applying a bond coating onto the substrate (74); wherein the external coating (76',78') is applied onto the bond coating; and wherein the diffuser section (104) is further formed through the bond coating.
  8. The manufacturing method of any of claims 4 to 7, wherein: the meter section (102) is formed in the substrate (74) using an electric discharge machining process; and the diffuser section (104) is formed in the external coating (76',78') and the substrate (74) using a laser machining process.
  9. The manufacturing method of any of claims 4 to 8, wherein the preform component (60') comprises a preform of an airfoil or a flowpath wall for the turbine engine.
  10. The method of any of claims 2 to 9, wherein: the substrate comprises metal; and the external coating comprises ceramic.
  11. An inspection method, comprising: providing a component of a turbine engine (20), the component comprising a plurality of cooling apertures (64), a first of the plurality of cooling apertures (64) including a diffuser section (104) and a meter section (102); scanning at least a portion of the component (60') with an imaging system (156) to provide scan data indicative of an internal structure of the portion of the component (60'); and processing the scan data to evaluate alignment between the diffuser section (104) and the meter section (102).
  12. The method of claim 3 or 11, further comprising indicating alignment of the diffuser section (104) and the meter section (102) where a centerline (118) of the diffuser section (104) is coincident with a centerline (106) of the meter section (102) at an interface between the diffuser section and the meter section.
  13. The method of claims 3, 11 or 12, further comprising indicating alignment of the diffuser section (104) and the meter section (102) where a lateral offset between the diffuser section (104) and the meter section (102) is less than a threshold.
  14. The method of claims 3, 11, 12 or 13, further comprising indicating misalignment of the diffuser section (104) and the meter section (102) where a lateral offset between the diffuser section (104) and the meter section (102) is greater than a threshold.
  15. The method of any preceding claim, wherein the imaging system (156) comprises a microwave imaging system (156).

Description

BACKGROUND OF THE DISCLOSURE TECHNICAL FIELD This disclosure (invention) relates generally to a turbine engine and, more particularly, to cooling apertures and formation and/or inspection thereof in a component of the turbine engine. BACKGROUND INFORMATION A gas turbine engine includes various fluid cooled components such as turbine blades and turbine vanes. Such fluid cooled components may include one or more cooling apertures extending through a sidewall of the respective component. Various methods are known in the art for forming cooling apertures. While these known cooling aperture formation methods have various benefits, there is still room in the art form improvement. SUMMARY OF THE DISCLOSURE According to an aspect of the present invention, 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. According to another aspect of the present invention, a method is provided involving an imaging system. During this method, a component is provided for a turbine engine. The component includes a substrate and a meter section of a cooling aperture formed in the substrate. At least a portion of the component is scanned using the imaging system to provide scan data indicative of an internal structure of the portion of the component, where the portion of the component includes the meter section. An operation is performed based on the scan data. According to still another aspect of the present invention, an inspection method is provided. During this method, a component of a turbine engine is provided. The component includes a plurality of cooling apertures. A first of the cooling apertures includes a diffuser section and a meter section. At least a portion of the component is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the component. The scan data is processed to evaluate alignment between the diffuser section and the meter section. The following optional features may be applied to any of the above aspects. The imaging system may be configured as or otherwise include a microwave imaging system. The method may also include applying an internal coating onto a surface of the meter section prior to applying the external coating onto the substrate. The internal coating may be configured as or otherwise include an aluminide coating. The internal coating may be configured from or otherwise include PtAl. The internal coating may be configured from or otherwise include NiCoCrAlY. The substrate may be configured from or otherwise include metal. The external coating may be configured from or otherwise include ceramic. The method may also include applying a bond coating onto the substrate. The external coating may be applied onto the bond coating. The diffuser section may also be formed through the bond coating. The meter section may be formed in the substrate using an electric discharge machining process. The diffuser section may be formed in the external coating and the substrate using a laser machining process. The preform component may be configured as or otherwise include a preform of an airfoil for the turbine engine. The preform component may be configured as or otherwise include a preform of a flowpath wall for the turbine engine. The component may also include an external coating over the substrate. The operation may be or otherwise include forming a diffuser section of the cooling aperture in the external coating and the substrate based on the scan data. The component may also include an external coating over the substrate and a diffuser section of the cooling aperture formed in the external coating and the substrate. The operation may be or otherwise include evaluating an alignment between the diffuser section and the meter section based on the scan data. The method may also include 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. The method may also include 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. The method may also include 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. The present disclosure may include any on