高压涡轮叶尖压力侧开槽对气动换热特性的影响

Effect of High Pressure Turbine Pressure-side Groove Structure on Aerothermal Performance

带凹槽涡轮叶尖相比平叶尖会有更低的气动损失,然而在腔底的前半部分区域存在着高换热系数区。为了解决这一问题,通过研究凹槽叶尖压力侧设计槽结构对涡轮气热性能的影响,结合实验和数值模拟结果,结果表明具有压力侧槽结构的凹槽叶尖相比于没有槽结构的凹槽叶尖,高换热区面积减小,气动效率提升。同时,研究不同大小的槽对气热性能影响,结果表明通过槽进入腔内的气流量会大幅影响叶顶间隙和腔内的流场,叶尖区域换热及气动性能随着槽的大小的改变而不同。

Many studies have illustrated that the turbine blade with a squealer tip has less aerodynamic loss than the one with a flat tip.However,there is a high heat transfer coefficient(HTC)area in the front half of the cavity bottom.To solve the problem,the effect of squealer-rim pressure-side groove structure on turbine blade aerothermal performance was studied.Combining the experimental and numerical simulation results,it can be concluded that the tip of the groove with a pressure side groove structure is smaller than the groove tip without a groove structure,the area of the high heat transfer area is reduced,and the aerodynamic efficiency is improved.Meanwhile,by studying the effect of grooves of different sizes on the aerothermal performance,it is found that the air flow into the cavity through the groove will greatly affect the tip clearance and the flow field in the cavity.