A gas turbine engine component includes an airfoil defined by a leading edge, a trailing edge, a pressure sidewall, and a suction sidewall. An internal cavity extends radially through the airfoil and is partially defined by an inner surface of the pressure sidewall and an inner surface of the suction sidewall. A baffle is disposed within the internal cavity, and includes a baffle wall conformal with adjacent surfaces of the internal cavity, a divider separating a forward chamber and an aft chamber, and a plurality of orifices extending through the baffle wall at the forward chamber. At least one axial rib is disposed between the baffle wall and the internal cavity, and is positioned at a discrete spanwise location of the airfoil.