Airfoil with skin core cooling

A gas turbine engine component comprising:

• an outer platform and an inner platform, and an airfoil extending radially inwardly of said outer platform to said inner platform;
• a central passage formed within said airfoil and having an inlet end in said outer platform for receiving cooling air and an outlet end in said inner platform for delivering cooling air to a downstream use;
• said airfoil having a suction wall and a pressure wall, and said airfoil extending in an axial direction from a leading edge to a trailing edge;
• a suction skin core between said central passage and said suction wall and a pressure skin core between said central passage and said pressure wall;
• said central passage extends axially between a passage leading edge end spaced toward said leading edge and a passage trailing edge end spaced towards said trailing edge, and at least one of said skin cores extends axially beyond each of said ends;
• at least one core inlet, separate of said central passage, which communicates with the pressure skin core and a second core inlet separate of said central passage, which communicates with the suction skin core to provide air to said pressure and suction skin cores;
• wherein said core inlets are spaced towards said leading edge relative to said central passage;
• wherein both of said skin cores extend axially beyond both of said ends of said central passage;
• and
• wherein said suction skin core and said pressure skin core each having at least one bump extending toward the other of said suction skin core and said pressure skin core, respective, and between said passage leading edge end and said leading edge.