Abstract: A turbine cooling configuration of an aeroengine was simplified to a rotating cavity with a tangential preswirling fringe guide vane 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 flow pattern in the rotating cavity is mainly controlled by Rossby number.The averaged heat transfer coefficient on the main disk increases with the increase of cooling air Reynold number and Grashoff number,the increase of rotating Reynold number decreases the heat transfer coefficient at some regions of the Rossby number and causes it to increase at others.Two experimental correlations for different regions of Rossby number,are established for the averaged heat transfer coefficient on the main surface.