Four rows of cylinder film cooling holes were allocated at the turbine cascade endwall with axial blade chord of 21%

51% and 81% and upstream of leading edge of 9%

by the CFD method. The standard k-ε turbulence model was applied to simulate cooling effect of the endwall with single angle and compound angle film-holes.The results show that

the advantage of compound angle jet could be well demonstrated when the incidence angle αreached 30°

at which time the average cooling efficiency of the compound angle jet was 16. 4% higher than that of the single angle jet. With an increase in blowing rate

the cooing efficiency drop was getting slower. The compound angle jet will cause reverse asymmetric vortexes

which strengthens the wall-attachment of the film to some extent and is helpful to the steam film cooling.