Castings, casting cores, and methods

A gas turbine engine component comprising:

• an airfoil having:
• a leading edge;
• a trailing edge;
• a pressure side extending between the leading edge and trailing edge;
• a suction side extending between the leading edge and trailing edge;
• and
• one or more cooling passageways extending through the airfoil and comprising a trunk extending from an inlet,
• wherein:
• at said inlet, said trunk is at least partially surrounded by an additional passageway, said additional passageway having a concavity with a spanwise axis of curvature;
• in transverse section, the at least one additional passageway bends by at least 45°;
• and
• there are a first said additional passageway and a second said additional passageway cooperating to surround at least 300° of said trunk at said inlet.

A gas turbine engine component comprising:

• an airfoil having:
• a leading edge;
• a trailing edge;
• a pressure side extending between the leading edge and trailing edge;
• a suction side extending between the leading edge and trailing edge;
• and
• one or more cooling passageways extending through the airfoil and comprising a trunk extending from an inlet,
• wherein:
• at said inlet, said trunk is at least partially surrounded by an additional passageway, said additional passageway having a concavity with a spanwise axis of curvature;
• there are a first said additional passageway and a second said additional passageway cooperating to surround at least 300° of said trunk at said inlet;
• and
• the first said additional passageway and the second said additional passageway extend into the airfoil.