Hot section engine components having segment gap discharge holes

An airfoil for a gas turbine engine, the airfoil comprising:

• an airfoil body having an external side wall and an internal side wall and defining a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall;
• at least one segmented rib extending within the airfoil body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities are defined between the external side wall and the internal side wall, the at least one segmented rib comprising at least two rib segments separated by a segment gap;
• and
• a discharge hole formed in the external side wall fluidly connecting the segment gap to an exterior surface of the airfoil body, wherein a center of the discharge hole is aligned with a radially oriented axis of the at least two rib segments that define the segment gap.