多级轴流压气机嵌入级的试验与数值模拟

针对多级轴流压气机中复杂流场在数值模拟时存在计算精度的问题,以四级低速大尺寸轴流压气机为试验平台开展测试研究,并选取第三级带悬臂静叶的嵌入级,进行了与试验同一设计流量工况点的多通道定常和非定常数值模拟.试验与数值模拟结果对比研究表明,气流经过转静交接面时由于掺混损失造成总压降低;转静交接面对非定常计算得到的绝对气流角的...

Experimental and Numerical Simulation of the Embedded Stage of a Multistage Axial Compressor

Aiming at the problem of calculation accuracy in numerical simulation of complex flow field in multistage axial compressors, the experiment was conducted on a 4-stage low speed research compressor, and the embedded third stage with the cantilevered stator was simulated by RANS (Reynolds Averaged Navier-Stokes) and URANS (unsteady Reynolds Averaged Navier-Stokes) methods in multi-passages at the design point. The comparison between the experimental and numerical simulation results shows that the total pressure decreases due to the mixing loss when the airflow passes through the rotor-stator interface. The influence of the absolute flow angle obtained by URANS on the rotor-stator interface can be up to 2°, so the interface position for URANS calculation should be after the test measurement plane to ensure that the post-processing plane of simulation is consistent with the experimental measuring plane. The RANS results near the middle span of the stator are closer to the experimental values, while the URANS method is more accurate in the calculation of the total pressure and loss of the cantilevered stator blade near the hub region, which indicates that URANS can simulate the unsteady flow near the cantilevered stator hub more accurately than RANS.