跨声速压气机转子叶尖区域流动特性的数值研究  

Numerical Research of Flow Stability at Tip Region in Single-stage Transonic Axial Compressor

作　　者：刘震雄 Liu Zhenxiong(Shanghai Civil Aviation College,Shanghai 200232 China)

机构地区：[1]上海民航职业技术学院,上海200232

出　　处：《中国民航飞行学院学报》2022年第5期67-72,共6页Journal of Civil Aviation Flight University of China

摘　　要：本文采用全三维定常数值模拟的方法,对NASA Stage35跨声速压气机转子叶尖区域的流动特性进行研究,开展了网格独立性验证,通过与试验结果数据进行对比,确定了最优网格数量,核准了商用CFD软件的可靠性,计算获得的性能特性曲线和基元级性能与试验数据结果具有较好的一致性。通过对NASA Stage35转子叶尖区域流动特性分析表明:压气机发生流动失稳现象极有可能是由于在转子叶尖区域近压力面侧形成的低速流团堵塞叶栅通道造成的。在近失速工况,泄漏流和主流相互作用形成泄漏涡,泄漏涡和叶片前缘激波在流道中发生强烈干涉。同时,叶尖间隙泄漏涡经过激波后膨胀,间隙泄漏涡发生破碎,结构发生巨大变化,造成转子近叶尖区域的低速流团。Three-dimensional numerical simulations had been used to analyze the flow stability at tip region in NASA Stage 35 which was a typically single-stage transonic compressor.Firstly,the mesh grids and the numerical model validated with the experimental date to investigate the accuracy of the CFD code.The computed performance maps of the chosen optimum grid matched best with the experimental data.Then,the model was used to analyze the internal flow filed in the compressor stage.As a result,it found that the low speed fluid near pressure surface at rotor tip most likely induces the flow instability.At the pre-stall condition,the leakage flow vortex passed the shock and then broken,the structures of the vortex took place great changes,which leading to the low speed fluid near the rotor tip passage.

关 键 词：跨声速压气机 数值模拟 流动稳定性 叶尖泄漏流 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]