周向槽机匣处理对跨声速轴流压气机影响分析  

Analysis of the Effects of Circumferential Groove Casing Treatment on a Transonic Axial Flow Compressor

作　　者：党春宁[1] 

机构地区：[1]第二炮兵工程学院,陕西西安710025

出　　处：《燃气涡轮试验与研究》2008年第3期18-25,12,共9页Gas Turbine Experiment and Research

摘　　要：设计了一种周向槽机匣处理结构,并利用全三维定常数值模拟方法,研究了该机匣处理结构对某跨声速轴流压气机转子性能和流场的影响。结果表明,数值模拟结果与实验结果符合良好,该周向槽处理机匣使压气机转子的失速点流量减小了11.5%,有效地扩大了其稳定工作范围,但是同时也使得其峰值效率下降了0.82%。对压气机转子内部流场的分析表明,周向槽处理机匣扩稳的主要机理在于其对叶尖间隙泄漏涡与激波干扰后形成的低速流团的抑制,以及对叶片吸力面附面层径向涡在机匣面堆积形成的低速流团的吸除。A circumferential groove casing treatment was designed, the effects of circumferential casing treatment on the performance and flow field of a transonic axial flow compressor rotor was numerically investigated by performing a 3-D steady-state Navier-Stokes analysis. The results show that, the calculation agrees well with the experiment. The circumferential groove casing treatment is able to extend the stall margin of the compressor rotor effectively with slight penalty on the adiabatic efficiency. The stall mass flow and the peak adiabatic efficiency are degreased by 11.5 percent and 0.82 percent respectively. The analysis of the internal flow field indicates that, the key mechanism of circumferential groove to extend the stall margin is the supp leakage flow and passage shock, ression of blockage zone resulted from the interactions between the tip another key mechanism to extend the stall margin is the remove of blockage zone resulted from boundary layer radial vortex.

关 键 词：轴流压气机 数值模拟 周向槽处理机匣 气动稳定性 失速边界 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]