Vanes for gas turbine engines are described. The vanes include an airfoil body extending between a first platform and a second platform, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side and at least one skin core cavity comprising a first skin core cavity, wherein the first skin core cavity defines a throughflow passage through the vane between the first platform and the second platform, wherein the at least one skin core cavity is defined between an external hot wall of the vane and an internal cold wall of the vane.