A vane (300; 400; 500) for a gas turbine engine , the vane comprising: an airfoil body (302; 402; 502) extending between a first platform and a second platform , the airfoil body having a leading edge (310; 410), a trailing edge (312; 412), a pressure side (314; 414; 514), and a suction side (316; 416; 516); a first main body cavity arranged along a portion of the pressure side of the airfoil body, the first main body cavity defining a first main body cavity internal cold wall ; a plurality of suction side skin core cavities (464; 570, 574, 576) defined within the airfoil body along the suction side thereof, wherein at least one suction side skin core cavity of the plurality of suction side skin core cavities defines a throughflow passage through the airfoil body between the first platform and the second platform, wherein each suction side skin core cavity is defined between an external hot wall of the suction side and the first main body cavity internal cold wall of the vane; a second main body cavity aft of the first main body cavity and arranged along a portion of the suction side of the airfoil body, the second main body cavity defining a second main body cavity internal cold wall; a plurality of pressure side skin core cavities defined within the airfoil body along the pressure side thereof, wherein at least one pressure side skin core cavity of the plurality of pressure side skin core cavities defines a throughflow passage through the airfoil body between the first platform and the second platform, wherein each pressure side skin core cavity is defined between an external hot wall of the pressure side and the second main body cavity internal cold wall; and a third main body cavity located aft of the second main body cavity, wherein the first main body cavity, the second main body cavity, and the third main body cavity define a serpentine flow path through the airfoil body. an airfoil body (302; 402; 502) extending between a first platform and a second platform , the airfoil body having a leading edge (310; 410), a trailing edge (312; 412), a pressure side (314; 414; 514), and a suction side (316; 416; 516); a first main body cavity arranged along a portion of the pressure side of the airfoil body, the first main body cavity defining a first main body cavity internal cold wall ; a plurality of suction side skin core cavities (464; 570, 574, 576) defined within the airfoil body along the suction side thereof, wherein at least one suction side skin core cavity of the plurality of suction side skin core cavities defines a throughflow passage through the airfoil body between the first platform and the second platform, wherein each suction side skin core cavity is defined between an external hot wall of the suction side and the first main body cavity internal cold wall of the vane; a second main body cavity aft of the first main body cavity and arranged along a portion of the suction side of the airfoil body, the second main body cavity defining a second main body cavity internal cold wall; a plurality of pressure side skin core cavities defined within the airfoil body along the pressure side thereof, wherein at least one pressure side skin core cavity of the plurality of pressure side skin core cavities defines a throughflow passage through the airfoil body between the first platform and the second platform, wherein each pressure side skin core cavity is defined between an external hot wall of the pressure side and the second main body cavity internal cold wall; and a third main body cavity located aft of the second main body cavity, wherein the first main body cavity, the second main body cavity, and the third main body cavity define a serpentine flow path through the airfoil body. <EOS>