| Citation: | HU Yuqi, ZHENG Wentao, XIA Kailong, et al. Study of effect of insert-plate inlet distortion on performance and stability of counter-rotating fans[J]. Journal of Aerospace Power, 2026, 41（X）：20250483 doi: 10.13224/j.cnki.jasp.20250483
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In order to investigate the effects of total pressure inlet distortion on the performance and stability of a counter-rotating fan, numerical simulations were conducted on the aerodynamic performance and flow field characteristics of a two-stage counter-rotating lift fan under both uniform inflow and total pressure distorted inflow conditions behind a baffle. By combining steady and unsteady calculations, a comparative analysis was performed to explore the Instability mechanism of the counter-rotating fan under total pressure distorted inflow. The results indicate that under distorted inflow conditions, the internal flow of the fan exhibits stronger unsteadiness, leading to a flow rate shift and variation in the characteristic curves obtained from steady and unsteady calculations. Therefore, the stall condition of the fan under distorted inflow should be determined based on the results from unsteady calculations. Compared with uniform inflow conditions, the distorted inflow lowers the stall boundary mass flow rate from 175.82 kg/s to 162.69 kg/s, a reduction of 7.47%, and decreases the stall margin by 9.07%. The operational range within which the counter-rotating fan can stably operate is significantly reduced, and its ability to suppress stall disturbances has decreased. Before the onset of instability, as the total pressure distortion behind the baffle propagates downstream the circumferential extent of the distorted region remains largely unchanged. Consistent with uniform inflow conditions, the instability of the fan under total pressure distorted inflow behind the baffle first occurs in the tip region of the second-stage rotor R2. After blocking the R2 passage, it propagates upstream and affects the tip region of the first-stage rotor R1, leading to global instability.
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