对涡旋流影响压气机转子性能和稳定性的研究

发布时间：2018-06-17 04:49

本文选题：压气机 + 跨声速　；参考：《推进技术》2016年04期

【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 study the mechanism of vortex flow affecting the performance and stability of transonic axial compressor, a vane swirl generator was designed, and the combined numerical simulation of vortex generator and transonic single rotor was carried out. The results show that the smaller the number of swirl generator blades, the lower the vortex intensity, the smaller the total pressure ratio, the peak efficiency, the stable working range and the blockage boundary flow rate, and the larger the stall boundary flow. When the vortex intensity is equal to 60 掳, the peak efficiency and blocking boundary flow are reduced by 1.11% and 2.12 respectively, the stall boundary flow increases by 4.17%, the angle of attack increases and the relative Mach number of inlet decreases due to the coaxial vortex, and the inlet angle of attack decreases by reverse vortex. The inlet relative Mach number increases, and the axial velocity of the front edge of the vortex is low, which results in the sharp increase of the inlet angle of attack of the tip and the serious clogging of the tip leakage flow, which leads to the instability of the tip leakage flow at the front edge of the blade.
【作者单位】：南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室;先进航空发动机协同创新中心;
【基金】：南京航空航天大学青年科技创新基金(NS2014021)
【分类号】：V233

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