Abstract: A two dimensional compressible computer program was developed to predict the influence of the coolant ejection on the aerodynamic performance in transonic turbine cascade.The code was applied to the computation of energy loss coefficient for two different trailing edge ejection configurations.The results show that:(1)The energy loss coefficient for the ejection thuough the trailing edge holes would be higher than that for the ejection on the pressure side near the trailing edge.(2)The trailing edge ejection has no significant influence on the exit flow angle.(3)The energy loss decreases a little and then increases with increasing coolant mass ratio after a definite point.

Key words: Aircraft engine;Turbine cascade;Cascade wake;Wake interaction;Aerodynamic characteristic;Energy loss

摘要： 通过尾缘喷气模型与涡轮叶栅流场计算及附面层参数的关联 ,初步提供了能较为准确预测尾缘冷气喷射对尾迹参数分布规律及气动性能影响的理论预测系统。对半开缝和对开缝两种尾缘冷气喷射的研究表明 :喷气流量比增大时 ,两种不同形式叶栅的能量损失系数都有先减小后增大的趋势 ;在相同条件下 ,半开缝叶栅的能量损失系数比对开缝在相应条件下的要稍小一些 ;尾缘喷射对于叶栅的平均出口气流角的影响很小

关键词: 航空发动机;涡轮叶栅;叶栅尾流;尾流干扰;气动特性;能量损失