In most gas turbines, blade-cooling air is supplied from stationary preswirl nozzles that swirl the air in the direction of rotation of the turbine disk. In the ''cover-plate'' system, the preswirl nozzles are located radially inward of the blade-cooling holes in the disk, and the swirling air flows radially outward in the cavity between the disk and a cover-plate attached to it. In this combined computational and experimental paper; an axisymmetric elliptic solver, incorporating the Launder-Sharma and the Morse low-Reynolds-number k-epsilon turbulence models, is used to compute the flow, and heat transfer. The computed Nusselt numbers for the heated "turbine disk" are compared with measured values obtained from a rotating-disk rig. Comparisons are presented for a wide range of coolant flow rates, for rotational Reynolds numbers in the range 0.5 x 10(6) to 1.5 x 10(6), and for 0.9 < beta(p) < 3.1, where beta(p) is the preswirl ratio (or ratio of the tangential component of velocity of the cooling air at inlet to the system to that of the disk). Agreement between the computed and measured Nusselt numbers is reasonably good, particularly at the larger Reynolds numbers. A simplified numerical simulation is also conducted to show the effect of the swirl ratio and the other flow parameters on the flow and heat transfer in the cover-plate system.