| Citation: | CHEN Qi, HUANG Guoping, LIU Zepeng, et al. Study on coupling mechanism between offset paired vortex distortion and fan[J]. Journal of Aerospace Power, 2025, 40（6）：20230504 doi: 10.13224/j.cnki.jasp.20230504
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In accordance with the velocity and pressure distribution features of the offset paired vortex distortion at the exit of a typical large S-bend inlet, a method for defining the offset paired vortex boundary conditions was established by using a vortex model. The coupling effect mechanism between offset paired vortex distortion and fan was explored by carrying out numerical simulation research. From the research results, it indicated that the upstream distorted flow mixing was strengthened, and the tangential velocity increased under the suction effect of the fan. The condition of the offset paired vortex inlet caused the deterioration of fan performance, and a serious loss of stability margin. Among them, the loss of stability margin was 7.1% under the condition of mutual exclusion vortex with 35 m2/s vortex circulation, and 7.9% under the condition of mutual attraction vortex. As the strength of offset paired vortex increased, the fan performance deteriorated more, and the loss of stability margin was also greater. Under the condition of the offset paired vortex embodied in the large area of attack angle was caused by the axial speed loss and tangential pre-rotation of the fan blade tip. This caused a relatively high total pressure ratio in some blade channels of the fan, while the remaining positions of the fan were still at a relatively low total pressure ratio level, resulting in a decrease in the fan overall total pressure ratio near the stall point of the fan and an advance in the stall point.
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