应用计算流体动力学软件，以涡轮增压器自循环全工况性能试验为依据，计算了压气机级和涡轮级所承受的轴向力，并进一步对比了叶轮背盘有无篦齿的轴向力，分析了篦齿对轴向力的影响。研究表明：对于增压器自循环试验而言，大部分工况下涡轮增压器轴向力方向是由涡轮端指向压气机端，在低转速区某些工况，轴向力方向会反向；影响叶轮及涡轮表面压力大小及分布的因素，会对轴向力产生一定影响；由于齿腔对流体的动能有一定的耗散作用，影响了轮背壁面高速旋转所引起的气流速度和压力的径向分布，交错篦齿结构能够抵消部分蜗舌和压气机壳几何周向非均匀性对流动的影响，使轮背压力分布更为均匀。

Based on the self-cycle performance test of turbocharger, the axial thrust of the compressor stage and turbine stage were calculated by using the computational fluid dynamics software, and the axial thrust with or without labyrinth on the impeller back plate was further compared and analyzed. The research shows that the axial thrust direction of turbocharger is from turbine to compressor under most working conditions and will reverse in low speed region. The factors affecting the magnitude and distribution of impeller and turbine surface pressure will have a certain impact on the axial thrust. The cavity of staggered labyrinth has a certain dissipation effect on the kinetic energy of fluid and hence affects the radial distribution of air velocity and pressure caused by the high-speed rotation of the back wall of impeller. The staggered labyrinth structure can counteract the influence of volute tongue and compressor geometric circumferential non-uniformity on the flow to make the distribution of wheel back pressure more uniform.