Aspects of the disclosure are directed to a gas turbine engine internally cooled component airfoil having a peripheral wall having an external surface comprising a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from a proximate end to a distal end. The gas turbine engine internally cooled component airfoil may include a cooling system having at least one or more passages bounded in part by the peripheral wall, where at least a first of the one or more passages includes a first passage pressure side surface that includes an interior protrusion including a first sloped surface extending to a peak of the interior protrusion and a second sloped surface extending from the peak substantially in the direction of the pressure side surface. The slope of the second sloped surface may be greater than the slope of the first sloped surface and a first cooling hole extends from the second sloped surface through the interior protrusion to vent the first of the one or more passages to the pressure side surface.