To investigate the effect of vertex shedding frequency on heat transfer and gas film cooling of the rotor blade

on the basis of Simple algorithm

the SSTk-ωturbulence model and finite volume method were adopted to discrete the control equations.Under conditions with no film-cooling hole and three rows of film-cooling holes at front edge of the blade

the effect of rotor speed on gas film cooling performance was numerically studied.The rotor speeds of 500r/min

1 000r/min and 2 000r/min were selected as the simulation conditions.The Nusselt number distribution on rotor surface was obtained.The results show that

with the increasing rotor speed

there's dramatic difference in cooling effectness between the blade with no film-cooling hole and the one with three rows of film-cooling holes.For the rotor with no film-cooling hole

the Nusselt number on pressure side and suction side of the rotor reduced gradually with an increase in rotor speed

so the heat transfer performance was relatively poor.While for the rotor with three rows of filmcooling holes

the heat transfer was enhanced and the film cooling efficiency was higher.