Turbine engine component with cooling aperture

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

• an airfoil having an outer wall defining an interior, the outer wall having an interior surface facing the interior and an exterior surface opposite the interior surface;
• a cooling circuit at least partially defined by the interior to provide a flow of cooling fluid;
• and
• a cooling aperture fluidly coupled to the cooling circuit, the cooling aperture comprising:
• a cavity defining a volume;
• at least one metering hole that fluidly couples the cooling circuit and the cavity;
• a diffuser outlet exhausting from the cavity at the exterior surface and extending between a first opposing end and a second opposing end;
• a first side meeting the diffuser outlet at the first opposing end;
• and
• a second side meeting the first side at a junction, and the second side meeting the diffuser outlet at the second opposing end;
• wherein a first axis is defined extending from the junction to the first opposing end and projected onto a two-dimensional plane of the exterior surface;
• wherein a second axis is defined extending from the junction to the second opposing end and projected onto the two-dimensional plane;
• and
• wherein a cavity angle (α) is defined as an angle between the first axis and the second axis, and wherein the cavity angle (α) is greater than or equal to 75° and less than or equal to 135°.