对涡旋流影响压气机转子性能和稳定性的研究

Effects of Twin Swirl on Performance and

关键词:  压气机  跨声速  对涡  效率  稳定性

Key words:  Compressor  Transonic  Twin swirl  Efficiency  Stability

摘要:

为研究对涡旋流影响跨声速轴流压气机性能和稳定性的机理，设计了一种叶片式旋流发生器，并对旋流发生器和跨声速单转子进行了联合数值模拟研究。计算结果表明旋流发生器叶片数越少，对涡强度越低；对涡旋流导致压气机总压比、峰值效率、稳定工作范围和堵塞边界流量减小，失速边界流量增大，对涡强度等于60°时峰值效率和堵塞边界流量分别降低1.11%和2.12%，失速边界流量增加4.17%；对涡中的同向涡导致叶尖进口攻角增加，进口相对马赫数减小；反向涡使叶尖进口攻角降低，进口相对马赫数增大；对涡前缘的轴向速度偏低，造成叶尖进口攻角大幅增加，叶尖泄漏流堵塞严重；由于叶尖泄漏流在叶片前缘溢流导致失稳。

Abstract:

In order to investigate the effects of twin swirl on performance and stability of transonic axial compressor，blade swirl generator was designed and simulated with a transonic single rotor. The results show that the intensity of twin swirl can be decreased by reducing blade number. Total pressure ratio，maximum efficiency，stable operating range and choke mass flow are decreased by twin swirl，and mass flow at stall boundary increases greatly. Maximum efficiency and choke mass flow decrease by 1.11% and 2.12% respectively，and mass flow at stall boundary increases by 4.17% as swirl intensity equals to 60°. Co-rotating swirl drives increase in attack angle and causes loss in relative Mach number at tip regions. On the contrary，counter rotating swirl decreases attack angle and increases relative Mach number at tip areas. Axial velocity at leading edge of twin swirl is lower than other regions，which makes attack angle increase and tip leakage block more serious. Leading edge spillage of tip leakage flow leads to instability.