中文摘要：

数值研究低速条件下边界层吸除对某高负荷压气机叶栅气动性能的影响。对该高负荷压气机叶栅原型进行数值研究,通过与前期试验数据的对比,校核商业计算流体力学（Computational fluid dynamics,CFD）计算代码的可靠性。结果表明,计算得到的性能曲线与试验数据有较好的一致性,所应用的数值模拟手段是可行的;分析不同正冲角时叶栅出口总压损失的分布,并给出吸力面及端壁极限流线。结果表明,边界层吸除可有效改善叶栅气动性能,低能流体被吸除使得吸力面及角区的分离减小,且叶栅总压损失显著减小;随着冲角的增加,较小的吸气量不能实现叶栅性能较大的提升,需要增大吸气量才能有效削弱流动分离;在＋10°冲角时,边界层吸除对大分离情况下的流场控制作用明显减弱,小吸气量时甚至使得压气机气动性能恶化。

英文摘要：

The effects of boundary layer suction on the aerodynamic performance of low-speed compressor cascade with highly loading are numerically studied.The baseline compressor is considered to perform a numerical investigation and by comparing with the experimental data available from literature,the reliability of commercial computational fluid dynamics（CFD） computational code is validated.The results show that computed performance maps achieve a good agreement with the experimental data,so it＇s practicable by using the means of numerical simulations on the study.The distributions of exit total pressure loss at different positive incidences are analyzed,and the limited streamline at suction surface and end wall also are given.The results show that boundary layer suction improves effectively the aerodynamic performance of compressor cascade,and the flow separation at the corner will be restrained for low-energy flow aspirated,which results in the decrease of total pressure loss at exit.As incidence increases,greater performances improvement can＇t be achieved by a smaller suction rate,unless the suction flow rate is increased.At ＋10° incidence,the flow control ability is weaken for the strong separation condition by boundary layer suction,and the aerodynamic performance in compressor is even worse at a smaller suction rate.