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为了抑制气膜冷却过程中耦合涡的产生,本文提出了一种切向出流台阶缝冷却结构,并对其在涡轮导叶吸力面、压力面上布置时的气动性能及冷却特性进行了数值研究。结果表明:在吸力面叶栅通道喉部附近布置时仅使总压损失增加约2%;在压力面布置则能使总压损失、能量损失在低吹风比工况各降低约2.5%,同时出气角的增加不到0.1%,而且损失系数和出气角对吹风比的变化也不敏感。吸力面、压力面缝后冷却效率均较高,在高吹风比工况平均都有约8%轴向弦长的叶片表面冷效接近1.0。
In order to suppress the generation of coupling vortex during the film cooling, a tangential outflow step cooling structure is proposed and its aerodynamic performance and cooling characteristics when the turbine vane is placed on the suction side and the pressure side are numerically the study. The results show that only about 2% of the total pressure loss is increased when the suction cascade is arranged near the throat of the cascade. Total pressure loss and energy loss are reduced by 2.5% The increase of outlet angle is less than 0.1%, and the loss coefficient and outlet angle are also insensitive to the change of blowing ratio. The cooling efficiency of the suction side and the pressure side seam are both higher, and the average surface cooling efficiency of the blade with an axial chord of about 8% at the high blowing ratio is close to 1.0.