Apparatus, system, and method for inspecting a component

A system for inspecting a gas turbine engine component that has a plurality of cooling apertures, the system comprising:

• an apparatus comprising:
• a main body comprising:
• a plurality of body apertures configured to at least partially align with the plurality of cooling apertures of the gas turbine engine component, wherein each body aperture from the plurality of body apertures extends through the main body;
• and
• a plurality of aperture wall surfaces defining the plurality of body apertures, wherein each aperture wall surface from the plurality of aperture wall surfaces defines a corresponding body aperture from the plurality of body apertures;
• and
• a seal connected or connectable to the main body and configured to engage with the gas turbine engine component, the seal comprising a plurality of seal apertures corresponding to the plurality of body apertures, wherein each seal aperture from the plurality of seal apertures extends through the seal, and wherein the plurality of seal apertures is at least partially aligned with the plurality of body apertures of the main body, such that the plurality of seal apertures is disposed or disposable in fluid communication with the plurality of body apertures;
• and
• a thermography device configured to obtain thermal image data associated with a surface of the main body opposite to the seal and the plurality of aperture wall surfaces.

A method of inspecting a gas turbine engine component, the method comprising the steps of:

• providing a gas turbine engine component comprising a plurality of cooling apertures;
• providing an apparatus comprising:
• a main body comprising:
• a plurality of body apertures configured to at least partially align with the plurality of cooling apertures of the gas turbine engine component, wherein each body aperture from the plurality of body apertures extends through the main body;
• and
• a plurality of aperture wall surfaces defining the plurality of body apertures, wherein each aperture wall surface from the plurality of aperture wall surfaces defines a corresponding body aperture from the plurality of body apertures;
• and
• a seal comprising a plurality of seal apertures corresponding to the plurality of body apertures, wherein each seal aperture from the plurality of seal apertures extends through the seal, and wherein the plurality of seal apertures is at least partially aligned with the plurality of body apertures of the main body;
• connecting the seal to the main body, such that the plurality of seal apertures is disposed in fluid communication with the plurality of body apertures;
• engaging the gas turbine engine component with the seal of the apparatus, such that the plurality of cooling apertures aligns with the plurality of seal apertures;
• directing a flow of air through the plurality of cooling apertures;
• obtaining thermal image data associated with a surface of the main body opposite to the seal and the plurality of aperture wall surfaces;
• and
• determining an inspection parameter associated with the plurality of cooling apertures based on the thermal image data, the inspection parameter optionally being a blockage parameter.