采用非定常数值方法对低雷诺数条件下50%,75%和100%三种不同轴向叠合量的轴向倾斜缝处理机匣结构对NASA Rotor 37跨声速压气机转子的扩稳效果进行了研究.结果表明,引入处理机匣后,附面层径向涡得到了很好的抑制,由附面层径向涡所引发的叶顶阻塞区大为减小,虽然又引发了由叶顶间隙涡对叶顶所造成的阻塞,但引入处理机匣后对压气机稳定性仍有较大的改善,能有效提高压气机转子的失速裕度. The unsteady numerical method is used to analyze the effect of axial tilting seam casing with 50%, 75% and 100% axial overlap on the NASA Rotor 37 transonic compressor rotor under low Reynolds number conditions The results show that the radial vortex of the top coat is well restrained after the casing is introduced into the casing, and the obstruction of the top of the vane caused by the radial vortex of the top coat greatly decreases, However, the stability of the compressor is still greatly improved after the casing is introduced into the casing, which can effectively improve the stall margin of the compressor rotor.