Abstract: A turbine cooling configuration of an aero-engine was simplified to a rotating cavity with an axial fringe inlet and a radial outlet.The influences of rotating Reynold number,cooling air Reynold number and Grashoff number on the averaged heat transfer characteristics were experimentally investigated.The experiment indicated that the averaged heat transfer coefficient on the main disk increases with the increase of cooling air Reynold number and Grashoff number,and decreases with the increase of rotating Reynold number.An experimental correlation of the averaged heat transfer coefficient on the main surface is formulated.