An airfoil for a gas turbine engine, the airfoil comprising: an airfoil body extending between a first platform and a second platform; a first platform feed cavity defined by the first platform; a second platform exit cavity defined by the second platform; a second platform feed cavity defined by the second platform; a first platform exit cavity defined by the first platform; at least one aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform, at least one aperture formed in the first platform and fluidly connecting the first platform exit cavity to an exterior of the first platform, a leading edge cavity, and a trailing edge cavity arranged along a pressure side of the airfoil body to a trailing edge of the airfoil body, a first hybrid skin core cooling cavity passage is formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity; wherein the first hybrid skin core cooling cavity passage has a variable first cavity width that converges along a flow direction from the first platform feed cavity to the second platform exit cavity, the first hybrid skin core cooling cavity passage located within the airfoil body along a suction side of the airfoil body; the airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body; a second hybrid skin core cooling cavity passage is formed within the airfoil body and fluidly connecting the second platform feed cavity to the first platform exit cavity, the second hybrid skin core cooling cavity arranged adjacent the first hybrid skin core cooling cavity along the suction side of the airfoil body; and the airfoil body does not include any apertures fluidly connecting the second hybrid skin core cooling cavity passage to an exterior of the airfoil body; characterized in that: the at least one aperture formed in the second platform is a purge aperture; the at least one aperture formed in the first platform is a purge aperture; the first hybrid skin core cooling cavity passage is defined between a hot exterior surface of the airfoil body along the suction side of the airfoil and a cold interior wall that defines a wall of the trailing edge cavity; and wherein the second hybrid skin core cooling cavity passage is defined between a hot exterior surface of the airfoil body along the suction side of the airfoil and a cold interior wall that defines a wall of the trailing edge cavity. an airfoil body extending between a first platform and a second platform; a first platform feed cavity defined by the first platform; a second platform exit cavity defined by the second platform; a second platform feed cavity defined by the second platform; a first platform exit cavity defined by the first platform; at least one aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform, at least one aperture formed in the first platform and fluidly connecting the first platform exit cavity to an exterior of the first platform, a leading edge cavity, and a trailing edge cavity arranged along a pressure side of the airfoil body to a trailing edge of the airfoil body, a first hybrid skin core cooling cavity passage is formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity; wherein the first hybrid skin core cooling cavity passage has a variable first cavity width that converges along a flow direction from the first platform feed cavity to the second platform exit cavity, the first hybrid skin core cooling cavity passage located within the airfoil body along a suction side of the airfoil body; the airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body; a second hybrid skin core cooling cavity passage is formed within the airfoil body and fluidly connecting the second platform feed cavity to the first platform exit cavity, the second hybrid skin core cooling cavity arranged adjacent the first hybrid skin core cooling cavity along the suction side of the airfoil body; and the airfoil body does not include any apertures fluidly connecting the second hybrid skin core cooling cavity passage to an exterior of the airfoil body; characterized in that: the at least one aperture formed in the second platform is a purge aperture; the at least one aperture formed in the first platform is a purge aperture; the first hybrid skin core cooling cavity passage is defined between a hot exterior surface of the airfoil body along the suction side of the airfoil and a cold interior wall that defines a wall of the trailing edge cavity; and wherein the second hybrid skin core cooling cavity passage is defined between a hot exterior surface of the airfoil body along the suction side of the airfoil and a cold interior wall that defines a wall of the trailing edge cavity. the at least one aperture formed in the second platform is a purge aperture; the at least one aperture formed in the first platform is a purge aperture; the first hybrid skin core cooling cavity passage is defined between a hot exterior surface of the airfoil body along the suction side of the airfoil and a cold interior wall that defines a wall of the trailing edge cavity; and wherein the second hybrid skin core cooling cavity passage is defined between a hot exterior surface of the airfoil body along the suction side of the airfoil and a cold interior wall that defines a wall of the trailing edge cavity.