Film cooling on the blade surface plays an important role in protecting the turbine blades from the high entry temperature of around 2000K. The arrangement of cold stream injection holes with various hole diameter, pitch, and injection angle affects the heat transfer of film cooling. Due to the strong interaction of the centrifugal, Coriolis and viscous forces, the characteristics of film cooling on rotating body may have a large deviation from the stationary ones. Experiments were conducted to investigate the heat transfer of film cooling on a radially rotating cylinder cascade. In the experiment, one used rotating circular cylinder for simulating leading blunt-body of a turbine rotor blade. Furthermore, one utilized cold air-hot cylinder to simulate the real condition of hot air-cold blade heat transfer. The diameter of the test cylinder was 50 mm, the height was 140 mm. The discrete round holes were inclined outwards at an injection angle of 35 °. In this study, the range of parameters were the density ratio DR ≈ 1, the blowing ratio 0.2 < Β < 1.9, the Reynolds number 1.7 × 10⁴ < Re < 6. 7 × 10⁴, the rotational speed 0 ≤ Q ≤ 600 rpm.