为了降低在氢燃料电池离心压缩机跨音速运行时产生的涡流，根据国外高速流体机械的流场实验结果，基于雷诺时均理论，通过ANSYS CFX对跨音速下叶轮流道的流场特性进行了仿真计算，重点研究了跨音速叶片边界层发生转捩时的流场特性，并对离心叶片进行了结构优化。研究发现：叶轮在转速为120 000 r/min时流场处于跨音速状态，叶片入口处在激波与附面层相互用下不仅加速了叶片上的边界层分离，而且在流道入口处产生了大的宏观旋涡。通过在叶片前部加圆柱形涡流发生器可以增大边界层内流体的动能，提高流体在边界层内克服阻力的能力，改善跨音速叶片前端的附面层分离，实现较好的流动控制，削弱叶片前端大的旋涡流，改善流场的速度分布，在降低了能量损失的同时实现了叶片压力最大脉冲可降低约16.7%，为跨音速离心叶轮的研究提供了一定价值和指导意义。

To address the issue of vortices generated during transonic operation in hydrogen fuel cell centrifugal compressors, a study was conducted based on experimental flow field data from high-speed foreign fluid machinery and RANS (Reynolds-averaged Navier-Stokes) theory. Numerical simulations of the flow field characteristics in the impeller passage under transonic conditions were performed using ANSYS CFX. The focus was placed on analyzing the flow field during boundary layer transition on transonic blades and optimizing the centrifugal blade structure. The results show as follows. At an impeller rotational speed of 120 000 r/min, the flow field was observed to operate in a transonic regime. Due to the interaction between shock waves and the boundary layer at the blade inlet, it was found that boundary layer separation was accelerated, and large-scale vortices were generated at the passage inlet. By introducing cylindrical vortex generators near the blade leading edge, the kinetic energy of the boundary layer fluid was enhanced, enabling improved resistance to flow separation. This modification resulted in suppressed boundary layer separation at the blade front, optimized flow control, and weakened large-scale vortex structures. Additionally, the velocity distribution uniformity within the flow field was improved, leading to reduced energy losses. A reduction of approximately 16.7% in the maximum pressure pulsation was achieved, which provides valuable insights and methodological guidance for transonic centrifugal impeller research.