高压涡轮叶尖压力侧开槽对气动换热特性的影响

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。

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

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 exists an area of high heat transfer coefficient (HTC) in the frontal region of the cavity floor. To solve the problem, Tthe present study concentrates on the effect of squealer-rim pressure-side groove structure on turbine blade aerothermal performance. Through the experimental and CFD results, it can be concluded that the case with a groove on the pressure side of the squealer rim has smaller area of high heat transfer coefficient region and the aerodynamic efficiency is raised. Meanwhile, the effect of different sizes of the groove is also investigated and it has a great impact on the heat transfer and aerodynamics. It is found that tThe mass flow passing through the groove can largely influence the flow field of the tip gap and the cavity. The heat transfer and the aerodynamic efficiency of the blade tip vary from the groove size.