Previous numerical and experimental studies, assuming adiabatic airfoil and end wall surfaces, have shown that combustor hot streaks can cause significant temperature increases along the pressure surface of first-stage turbine rotors. In the current investigation, the combined effects of combustor hot streaks and airfoil heat transfer have been studied. The predicted results indicate that full-impingement of the hot streak on the first-stage stator results in low levels of heat transfer on the second-stage stator. Relatively high heat transfer on the first-stage rotor is localized to the leading edge and hub vortex and tip leakage flow regions. It is expected that alignment of the hot streak with the mid-passage of the first-stage stator would result in significant pressure-surface heat transfer on the first-stage rotor. These are the areas of the rotor which have been shown experimentally to endure the greatest thermal stresses.