MANUFACTURING METHOD FOR COATED COOLING APERTURES IN A TURBINE ENGINE COMPONENT

A manufacturing method (700) is provided. During this method (700), a preform component (60) is provided for a turbine engine (20). The preform component (60) includes a substrate (74'). A preform meter section (102') and a preform diffuser section (104') are formed in the substrate (74'). An internal coating (138') is applied to at least the preform meter section (102') to provide a meter section (102) of a cooling aperture (64). External coating material (94) is applied over the substrate (74'). The applying of the external coating material (94) forms an external coating (78) over the substrate (74'). The applying of the external coating (94) also builds up the external coating material (94) within the preform diffuser section (104') to form a diffuser section (104) of the cooling aperture (64).