A turbine engine airfoil element has: a plurality of spanwise main body passageways (210, 212, 214, 216, 218, 220, 222, 224, 226, 228) along a camber line (190); and a plurality of spanwise skin passageways (310, 312, 314, 316, 318, 320) along the pressure side (132). The spanwise skin passageways (310, 312, 314, 316, 318, 320) include: first skin passageways (310, 314, 320) each having a plurality of film cooling outlets (339) to the pressure side (132); and second skin passageways (316, 318, 320) each lacking film cooling outlets (339) to the pressure side (132). Linking passageways (334) extend between the first skin passageways (310, 314, 320) and the second skin passageways (316, 318, 320). The first skin passageways (310, 314, 320) and second skin passageways (316, 318, 320) are directly fed from one or more inlets of the airfoil element.