METHOD FOR FORMING COATED COOLING APERTURES IN A TURBINE ENGINE COMPONENT

A manufacturing method (800) is provided. During this method (800), a preform component (60) is provided for a turbine engine (20). The preform component (60) includes a substrate (74'). A meter section (102) of a cooling aperture (64) is formed in the substrate (74'). An internal coating (138') is applied onto a surface of the meter section (102). An external coating (78') is applied over the substrate (74'). A diffuser section (104) of the cooling aperture (64) is formed in the external coating (78') and the substrate (74') to provide the cooling aperture (64).