为研究涡轮增压器蜗壳进气结构对涡轮叶片激振力的影响，建立了涡轮机非定常流场模型进行计算分析，重点分析蜗壳非对称流场对涡轮叶片压力的干扰特性和激励来源，在此基础上提出了基于蜗壳进气结构优化的激振力弱化方案并进行了验证，分析了涡轮转子叶片表面压力波动的时域与频域特征。结果表明：蜗壳的非轴对称性和蜗舌的封闭作用影响蜗壳流场压力沿周向的分布，蜗舌后方的高静压区域是涡轮叶片激振的主要原因；蜗壳进气结构可以影响高静压区的压力峰值；提出的4种进气结构优化方案都能在几乎不影响涡轮机性能的前提下降低涡轮叶片的激振力，其中方案4叶片激振幅值减小了18.8%，为最优方案。

In order to explore the influence of turbocharger volute inlet structure on the turbine blade excitation force, the turbine unsteady flow field model was established for calculation and analysis. The interference characteristics and excitation sources of turbine blade pressure induced by the asymmetric flow field of volute were analyzed emphatically. The scheme of excitation force weakening based on volute inlet structure optimization was further proposed and verified. Then the time and frequency domain characteristics of pressure fluctuation on turbine blade surface were analyzed. The results show that the non-axisymmetry of volute and the sealing effect of volute tongue affect the circumferential distribution of pressure in the volute flow field and the high static pressure area behind the volute tongue is the main cause of turbine blade excitation. The volute inlet structure affects the pressure peak in the high static pressure zone. The four proposed optimization schemes of inlet structure can reduce the excitation force of turbine blades on the premise of hardly affecting the turbine performance. Among them, Case 4 blade excitation amplitude decreases by 18.8%, which is the optimal scheme.