An airfoil (400; 530) for a gas turbine engine, the airfoil comprising: an airfoil body (402; 532) extending between a leading edge (412; 542) and a trailing edge in an axial direction, between a pressure side (416; 538) and a suction side (418; 540) in a circumferential direction, and between a root and a tip in a radial direction; a first transitioning leading edge cavity (422; 534) located adjacent the pressure side proximate the root of the airfoil body and transitioning axially toward the leading edge as the first transitioning leading edge cavity extends radially toward the tip; and a second transitioning leading edge cavity (424; 536) adjacent the suction side and adjacent the leading edge proximate the root of the airfoil body and transitioning axially toward the trailing edge as the second transitioning leading edge cavity extends radially toward the tip; characterized in that: a portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the airfoil body such that the first transitioning leading edge cavity only cools the pressure side proximate the root, and in that the second transitioning leading edge cavity comprises a suction side portion and an impingement portion proximate the root, wherein the impingement portion of the second transitioning leading edge cavity shields the first transitioning leading edge cavity such that the temperature of the air within the first transitioning leading edge cavity is relatively cool as compared to the air within the second transitioning leading edge cavity at the root. an airfoil body (402; 532) extending between a leading edge (412; 542) and a trailing edge in an axial direction, between a pressure side (416; 538) and a suction side (418; 540) in a circumferential direction, and between a root and a tip in a radial direction; a first transitioning leading edge cavity (422; 534) located adjacent the pressure side proximate the root of the airfoil body and transitioning axially toward the leading edge as the first transitioning leading edge cavity extends radially toward the tip; and a second transitioning leading edge cavity (424; 536) adjacent the suction side and adjacent the leading edge proximate the root of the airfoil body and transitioning axially toward the trailing edge as the second transitioning leading edge cavity extends radially toward the tip; characterized in that: a portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the airfoil body such that the first transitioning leading edge cavity only cools the pressure side proximate the root, and in that the second transitioning leading edge cavity comprises a suction side portion and an impingement portion proximate the root, wherein the impingement portion of the second transitioning leading edge cavity shields the first transitioning leading edge cavity such that the temperature of the air within the first transitioning leading edge cavity is relatively cool as compared to the air within the second transitioning leading edge cavity at the root. a portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the airfoil body such that the first transitioning leading edge cavity only cools the pressure side proximate the root, and in that the second transitioning leading edge cavity comprises a suction side portion and an impingement portion proximate the root, wherein the impingement portion of the second transitioning leading edge cavity shields the first transitioning leading edge cavity such that the temperature of the air within the first transitioning leading edge cavity is relatively cool as compared to the air within the second transitioning leading edge cavity at the root.