Turbine engine component with a cooling aperture

A turbine blade assembly for a turbine engine, the turbine blade assembly comprising:

• an airfoil having an outer wall defining an interior of the airfoil and including an exterior surface;
• a cooling circuit in the interior;
• and
• a cooling aperture in the outer wall and fluidly coupled to the cooling circuit, the cooling aperture including:
• an impingement portion;
• a diffusion portion extending from the impingement portion and exhausting at a diffuser outlet at the exterior surface, wherein the diffuser outlet includes an upstream edge and a downstream edge, wherein a diffuser outlet height is defined as a distance between the upstream edge and the downstream edge within an intermediate region;
• a first side, a second side spaced from the first side, an outer surface extending between the first side and the second side, and an inner surface spaced from the outer surface and extending the first side and the second side, wherein the first side, the second side, the outer surface, and the inner surface at least partially define the impingement portion and the diffusion portion, wherein a diffuser outlet width is defined as a distance between the first side and the second side at the diffuser outlet;
• and
• a flared portion on the first side at the diffuser outlet.