A gas turbine engine component comprising: an airfoil defined by a leading edge, a trailing edge, a pressure sidewall, and a suction sidewall; an internal cavity extending radially through the airfoil and partially defined by an inner surface of the pressure sidewall and an inner surface of the suction sidewall; a baffle (75; 175; 275) disposed within the internal cavity, the baffle (75; 175; 275) comprising: a baffle wall (76; 176) conformal with adjacent surfaces of the internal cavity; a divider separating a forward chamber and an aft chamber; and a plurality of impingement orifices extending through the baffle wall (76; 176) at the forward chamber through which cooling fluid fed into the baffle (75; 175; 275) can pass into a region between the baffle (75; 175; 275) and the internal cavity; at least one axial rib disposed between the baffle wall (76; 176) and the internal cavity and positioned at a discrete spanwise location of the airfoil; characterised by further comprising: a cover plate located at a radially outer end of the component adjacent a cooling inlet and disposed to cover the aft chamber; and a cover plate located at a radially inner end of the component and disposed to cover the forward chamber, wherein the component is configured such that in use cooling fluid (F C) is radially introduced to the component at an inlet at a radially outer platform of the component to the forward chamber of the baffle (75; 175; 275) and is prevented from also entering the aft chamber by the cover plate located at the radially outer end; and wherein the component is configured such that the cooling fluid (F C) flows radially to and exits the component from an outlet end of the aft chamber at a radially inner platform of the component. an airfoil defined by a leading edge, a trailing edge, a pressure sidewall, and a suction sidewall; an internal cavity extending radially through the airfoil and partially defined by an inner surface of the pressure sidewall and an inner surface of the suction sidewall; a baffle (75; 175; 275) disposed within the internal cavity, the baffle (75; 175; 275) comprising: a baffle wall (76; 176) conformal with adjacent surfaces of the internal cavity; a divider separating a forward chamber and an aft chamber; and a plurality of impingement orifices extending through the baffle wall (76; 176) at the forward chamber through which cooling fluid fed into the baffle (75; 175; 275) can pass into a region between the baffle (75; 175; 275) and the internal cavity; a baffle wall (76; 176) conformal with adjacent surfaces of the internal cavity; a divider separating a forward chamber and an aft chamber; and a plurality of impingement orifices extending through the baffle wall (76; 176) at the forward chamber through which cooling fluid fed into the baffle (75; 175; 275) can pass into a region between the baffle (75; 175; 275) and the internal cavity; at least one axial rib disposed between the baffle wall (76; 176) and the internal cavity and positioned at a discrete spanwise location of the airfoil; characterised by further comprising: a cover plate located at a radially outer end of the component adjacent a cooling inlet and disposed to cover the aft chamber; and a cover plate located at a radially inner end of the component and disposed to cover the forward chamber, wherein the component is configured such that in use cooling fluid (F C) is radially introduced to the component at an inlet at a radially outer platform of the component to the forward chamber of the baffle (75; 175; 275) and is prevented from also entering the aft chamber by the cover plate located at the radially outer end; and wherein the component is configured such that the cooling fluid (F C) flows radially to and exits the component from an outlet end of the aft chamber at a radially inner platform of the component. a cover plate located at a radially outer end of the component adjacent a cooling inlet and disposed to cover the aft chamber; and a cover plate located at a radially inner end of the component and disposed to cover the forward chamber, wherein the component is configured such that in use cooling fluid (F C) is radially introduced to the component at an inlet at a radially outer platform of the component to the forward chamber of the baffle (75; 175; 275) and is prevented from also entering the aft chamber by the cover plate located at the radially outer end; and wherein the component is configured such that the cooling fluid (F C) flows radially to and exits the component from an outlet end of the aft chamber at a radially inner platform of the component.