Numerical simulation on unsteady film cooling process of high pressure turbine shroud under high speed blade sweep was conducted. The slip mesh was used to realize relative motion between the turbine blade and the turbine shroud wall. The effects of blade rotation

blowing ratio

rotation speed and reverse flow arrangement of gas film holes on cooling characteristics of the high pressure turbine shroud's gas film were analyzed. The results show that

the relative motion between the blade and the turbine shroud makes the cooling film distribution more uniform

and leads to gourd-shaped distribution of the film holes near the suction surface

which is conducive to the cooling of the turbine shroud. The reverse distribution of the gas film holes has better film cooling effect at high blowing ratio and higher rotating speed. The increase in blowing speed strengthens the gourd-shaped air film distribution under the action of tip leakage vortex

while weakens the compression effect of tip leakage vortex on cool air.