Abstract: A turbine cooling configuration of an aero-engine was simplified into a rotating cavity with an axial fringe inlet and a radial outlet.The influences of rotating Reynolds number,cooling air Reynolds number and Grashoff number on the local heat transfer and flow characteristics were investigated experimentally.The results indicated that the local heat transfer coefficient on the edge of main disk rapidly increases with the increase of cooling air Reynolds number and rotating Reynolds number.The local heat transfer coefficient becomes negative near the center of the disk.The flow friction coefficient increases with the increase of the cooling air Reynolds number and decreases with the rotating Reynolds number.