An airfoil for a gas turbine engine, the airfoil comprising: an airfoil body extending between a leading edge and a trailing edge in an axial direction, between a pressure side and a suction side in a circumferential direction, and between a root and a tip in a radial direction; a first shielding sidewall cavity located adjacent one of the pressure side and the suction side proximate the root of the airfoil body and extending radially toward the tip; a second shielding sidewall cavity located adjacent the other of the pressure side and the suction side proximate the root of the airfoil body and extending radially toward the tip; a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity proximate the root; and a main body cavity located aft of the first shielding sidewall cavity, the second shielding sidewall cavity, and the shielded sidewall cavity, wherein the main body cavity extends to the trailing edge of the airfoil body, wherein the first shielding sidewall cavity transitions aftward at a transition portion and extends from the root to the tip, and wherein the shielded sidewall cavity is not adjacent either of the pressure side or the suction side proximate the root such that the shielded sidewall cavity has no direct thermal contact with exterior surfaces of the airfoil body because the shielded sidewall cavity is between the first shielding sidewall cavity and the second shielding sidewall cavity, and the shielded sidewall cavity transitions toward the pressure or suction side radially outward from the transition portion to be proximate at least one of the pressure side and the suction side proximate the tip such that the shielded sidewall cavity provides cooling to outer diameter portions of the airfoil. an airfoil body extending between a leading edge and a trailing edge in an axial direction, between a pressure side and a suction side in a circumferential direction, and between a root and a tip in a radial direction; a first shielding sidewall cavity located adjacent one of the pressure side and the suction side proximate the root of the airfoil body and extending radially toward the tip; a second shielding sidewall cavity located adjacent the other of the pressure side and the suction side proximate the root of the airfoil body and extending radially toward the tip; a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity proximate the root; and a main body cavity located aft of the first shielding sidewall cavity, the second shielding sidewall cavity, and the shielded sidewall cavity, wherein the main body cavity extends to the trailing edge of the airfoil body, wherein the first shielding sidewall cavity transitions aftward at a transition portion and extends from the root to the tip, and wherein the shielded sidewall cavity is not adjacent either of the pressure side or the suction side proximate the root such that the shielded sidewall cavity has no direct thermal contact with exterior surfaces of the airfoil body because the shielded sidewall cavity is between the first shielding sidewall cavity and the second shielding sidewall cavity, and the shielded sidewall cavity transitions toward the pressure or suction side radially outward from the transition portion to be proximate at least one of the pressure side and the suction side proximate the tip such that the shielded sidewall cavity provides cooling to outer diameter portions of the airfoil.