The Realizable k-εturbulence model was adopted to investigate the cooling efficiency and streamlines of gas film on turbine blade surface with different blowing ratios.The jet holes on both sides of the stagnation line in front edge adopted negative angle opposed blowing

and other holes used compound angle blowing withαof 30°andβof 45°.Define that the blade surface is noslip adiabatic wall

the mainstream temperature Tm is 473.15Kand the jet-flow temperature Tc is293.15K.The results revealed that

with an increase in blowing ratio

for pressure surface of the static blade

the cooling efficiency of gas film increased sharply while that at front edge of the blade increased slightly;for suction surface of the blade

continuous film was formed

resulting in high cooling efficiency of the gas film.Using single angle cross-row configuration for jet holes at both sides of the stagnation line could enhance the film cooling efficiency

but with this method the jet disturbance to the main stream was strong.The advantage of compound angle jet could be well demonstrated when the local velocity of main stream was high.