跨音速轴流压气机转子泄漏特性研究

Effects of tip clearance flow on aerodynamic performance of transonic axial compressor rotor

以跨音速转子Rotor37为例,采用适合于求解轴流压气机内部三维湍流场的时间推进计算程序,对7种不同叶顶间隙下压气机转子叶栅通道内部湍流场进行数值模拟,研究转子气动性能随叶顶间隙的变化规律。结果表明:随着叶顶间隙减小,转子绝热效率和压比提高,稳定运行区域明显增大;叶顶间隙变化对压气机转子70%叶高至叶顶范围内的气动性能影响显著;转子气动性能随间隙变化并非简单的线性关系;综合考虑轴流压气机气动和强度要求,对于所研究的转子,最佳的叶顶间隙为0.178mm。

On the basis of a time-marching code in house,the internal three-dimensional turbulent flow field of a transonic axial compressor Rotor3 7 with seven tip clearances is numerically studied.The effects of tip clearance flow on aerodynamic performance of the transonic axial compressor rotor are investigated.The re-sults show that,with a decrease in the tip clearance,the aerodynamic efficiency and pressure ratio increase and the stable operation area enlarges significantly.The relationship between the aerodynamic performance and the tip clearance deviates far away from the linear function and appears the curve characteristics.For this rotor,the optimal tip clearance 0.178 mm is a compromise between aerodynamic and structural require-ments.