中文摘要：

对某型低速轴流压气机转子和NASA Rotor 37跨声速转子进行了全通道定常和非定常数值仿真研究,采用了喷管模型和节流阀模型作为出口边界条件来取代常规的边界条件设置方法,分别通过调节计算域出口面积和节流系数的方法改变转子工作状态。计算结果显示：与出口边界采用固定背压值的方法相比,采用喷管模型和节流阀模型能够准确计算转子失速前后各个工况点的流动状态。采用节流阀模型时,通过调节节流系数能够准确地判定转子失速临界点,在继续节流的过程中能够计算出失速时转子通道内失速区的形成与发展情况。研究发现,叶尖区域流动失稳即叶尖局部回流区的出现和扩展在这两型压气机转子的失速过程中起重要作用。其中低速轴流压气机转子全通道非定常计算发现,在失速时转子叶尖部位首先出现两处回流区,且回流区范围随转数增加而扩大,最终形成相对明显的失速团结构。

英文摘要：

Full annulus steady and transient numerical simulations are performed on a low-speed axial-flow compressor isolated-rotor test rig and NASA Rotor 37. Two new boundary methods, i.e. nozzle outlet and throttle outlet, are adopted instead of the traditional outlet boundary condition. The rotors operation point can be adjusted by changing the computation domaiffs outlet area and throttle coefficient individually. The simulation results show that compared with the traditional method, the two new methods can calculate the rotor flow field under all mass flow status, including the near stall status and after stall status. By adjus- ting the throttle coefficient, the ＂throttle outlet＂ model can capture the critical stall point accurately, and by so doing this can figure out the way how reversed flow region emerges and develops in the rotor passa- ges. The research finds that the instability flow structure in the blade tip region,i.e, the local reverse flow regions＂ formation and expansion processes, plays an important role in the two compressor rotors＂ stall characteristics. The full-annulus transient numerical simulation of the low-speed axial-flow compressor isolated-rotor finds that once the rotor comes to the stall state, two stall regions arise in the blade tip. The two stall regions expand with the increase of rotor revolutions, and the relatively significant stall regions come into being at last.