倒角和间隙对跨音轴流压气机气动性能的影响

The Influence of Blade Root Fillet and Blade Tip Clearance on the Aerodynamic Performance of a Transonic Axial Compressor

通过对一单级跨音速轴流压气机的流场进行数值模拟,研究了动叶根部倒角以及顶部间隙对流场气动性能的影响。结果表明:动叶叶顶间隙会造成顶部区域的通流阻塞并加重顶部分离损失,根部倒角会减小根部的气流折转角,降低做功能力,而且扩大根部分离区,减小根部流量,增大根部分离损失,因此为了提高数值模拟的准确性应考虑动叶叶顶间隙和根部倒角。

Through the numerical simulation of the flow field of a single-stage transonic axial compressor a study was conducted of the impact of rotating-blade root fillet and tip clearance on the flow field aerodynamic performance.The results of the study indicate that the blade tip clearance will lead to a flow blockage at the top zone and increase the separation loss at that zone.The blade root fillet will decrease the flow turning angle at the blade root,decrease work-performing capacity and enlarge the blade root separation zone.This will lead to a decrease in flow rate and an increase in separation loss at the root zone.In view of the above,the rotating blade tip clearance and the blade root fillet should be taken into account in order to enhance the accuracy of the numerical simulation.