An airfoil for a gas turbine engine, the airfoil comprising: an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending axially between a leading edge and a trailing edge, wherein the plurality of cavities comprise a leading edge hybrid cavity formed within the airfoil body extending in a radial direction between the first end and the second end of the airfoil body along the leading edge; an airfoil pressure side hybrid cavity located toward the trailing edge of the airfoil body relative to the leading edge hybrid cavity and positioned adjacent a pressure side wall of the airfoil body, wherein the airfoil pressure side hybrid cavity extends in a radial direction between the first end and the second end of the airfoil body; and an airfoil suction side hybrid cavity located toward the trailing edge of the airfoil body relative to the leading edge hybrid cavity and positioned adjacent a suction side wall of the airfoil body, wherein the airfoil suction side hybrid cavity extends in a radial direction between the first end and the second end of the airfoil body; a first divider rib extending radially between the first end and the second end of the airfoil body along the side wall of the airfoil body between the airfoil pressure side hybrid cavity and the leading edge hybrid cavity, a second divider rib extending radially between the first end and the second end of the airfoil body along the side wall of the airfoil body between the airfoil suction side hybrid cavity and the leading edge hybrid cavity, and an interior cavity within the airfoil body and located aft of the leading edge hybrid cavity, the interior cavity providing a cold wall to each of the leading edge hybrid cavity and the airfoil side hybrid cavities, wherein first cross-over holes are formed within the first divider rib to fluidly connect the airfoil pressure side hybrid cavity to the leading edge hybrid cavity, and wherein second cross-over holes are formed in the second divider rib to fluidly connect the airfoil suction side hybrid cavity to the leading edge hybrid cavity; characterised in that the first cross-over holes and the second cross-over holes are angled in a forward, radially outward direction to direct an airflow from the respective airfoil side hybrid cavity into the leading edge hybrid cavity. an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending axially between a leading edge and a trailing edge, wherein the plurality of cavities comprise a leading edge hybrid cavity formed within the airfoil body extending in a radial direction between the first end and the second end of the airfoil body along the leading edge; an airfoil pressure side hybrid cavity located toward the trailing edge of the airfoil body relative to the leading edge hybrid cavity and positioned adjacent a pressure side wall of the airfoil body, wherein the airfoil pressure side hybrid cavity extends in a radial direction between the first end and the second end of the airfoil body; and an airfoil suction side hybrid cavity located toward the trailing edge of the airfoil body relative to the leading edge hybrid cavity and positioned adjacent a suction side wall of the airfoil body, wherein the airfoil suction side hybrid cavity extends in a radial direction between the first end and the second end of the airfoil body; a first divider rib extending radially between the first end and the second end of the airfoil body along the side wall of the airfoil body between the airfoil pressure side hybrid cavity and the leading edge hybrid cavity, a second divider rib extending radially between the first end and the second end of the airfoil body along the side wall of the airfoil body between the airfoil suction side hybrid cavity and the leading edge hybrid cavity, and an interior cavity within the airfoil body and located aft of the leading edge hybrid cavity, the interior cavity providing a cold wall to each of the leading edge hybrid cavity and the airfoil side hybrid cavities, wherein first cross-over holes are formed within the first divider rib to fluidly connect the airfoil pressure side hybrid cavity to the leading edge hybrid cavity, and wherein second cross-over holes are formed in the second divider rib to fluidly connect the airfoil suction side hybrid cavity to the leading edge hybrid cavity; characterised in that the first cross-over holes and the second cross-over holes are angled in a forward, radially outward direction to direct an airflow from the respective airfoil side hybrid cavity into the leading edge hybrid cavity.