支板势干涉下压气机叶片瞬态强迫响应分析

The research focuses on the back 1.5 stage and the transition section equipped with struts of a multistage low-pressure compressor. The transient forced response of rotor blade in the final stage due to potential interference from the downstream strut was investigated using a one-way fluid-structure coupling method. Detailed analysis was conducted on the impact of strut potential disturbances on the unsteady flow field and flow loss of the upstream blade row. The results show that the strut has a significant blocking effect on the flow field at the stator outlet, which can aggravate or inhibit the flow separation of stator, and the effect decreases with the increase of the circumferential distance. Potential interference from the downstream strut introduces significant unsteady disturbances to the final rotor blades. Resonance occurs when the disturbance frequency closely matches the natural frequency of the blade. The stator blades located between the rotor and the strut significantly amplify the potential disturbances caused by the strut.