吸力面不同吹风比切向冷气喷射对跨声速涡轮叶栅气动性能的影响

In order to further clarify the effects of tangential coolant ejection on suction side on aerodynamic performance and film cooling effectiveness in a transonic turbine, numerical simulations were conducted on a transonic turbine cascade. Coolant slots were located at different positions on the suction side of blade and coolant was ejected at different blowing ratios to study the effects of tangential coolant slot on overall performance and de- tail of flow field of a transonic turbine cascade. The results showed that the tangential coolant ejection on suction side is good for minimizing the shock wave loss. The max Mach number can be reduced by more than 0.104. The energy loss coefficient has its minimum value when the coolant slot is placed upstream of the reflecting point of inner-extending shock wave and blowing ratio is between 0.75 to 1.00. The increasement of blowing ratio is beneficial to decrease the size of separation bubble inside the cooling slot, or even eliminate it. At the same time, the increasing blowing ratio is also good for decreasing the intensity of shock wave at the lip of cooling slot.