关键词: 跨声速涡轮叶栅;尾缘冷却;冷却流量;尾缘激波系;叶栅性能

Abstract: To find out the effect of the cooling method on aerodynamic characteristic in transonic turbine,the influence of the two kinds of transonic turbine cascade trailing edge cooling methods,pressure side ejection (PSEJ) and trailing edge ejection (TEEJ),on the cascade performance and trailing edge shock system structure has been researched in numerical simulation.The results indicate that,both methods reduce the cascade energy loss coefficient.The PSEJ style has better effect,and for the optimal case,the loss coefficient decreases up to 48%.The coolant mass flow has effect to some extent and there is a optimal value.The introduction of the trailing edge cooling changes the trailing edge shock system obviously,especially for the PSEJ method.The previous pressure side leg of the shock system has been split to three legs.

Key words: Transonic turbine cascade;Trailing edge cooling method;Coolant mass flow;Trailing edge shock system;Cascade performance