| Citation: | GAO Qian, YANG Xiaohe, LIU Shiwen. Experiment on inlet distortion of high bypass ratio fan and booster[J]. Journal of Aerospace Power, 2025, 40（2）：20230381 doi: 10.13224/j.cnki.jasp.20230381
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Based on a high bypass ratio turbofan engine, experimental investigation on the inlet total pressure distortion of the fan performance was carried out to obtain the fan-booster performance under crosswind conditions and support the engine crosswind test. The inlet total pressure distortion flow under the crosswind conditions was obtained by installing distortion simulation network. The distortion pattern was derived from the wind tunnel test of the engine nacelle. The total pressure distortion pattern included radial distortion and circumferential distortion. The results showed that the total pressure distortion raised the working point of the fan and reduced the surge margin. Compared with the fan performance of uniform flow, the corrected mass flow and total pressure ratio tended to increase, the mass flow ranged from 0.2% to 1%, while the corrected rotational speed ranged from 0.3 to 0.8. The core performance of the inlet total pressure distortion was similar with the performance of uniform flow. The static pressure of inlet total pressure distortion increased rapidly after the fan, and the static pressure behind the struts was basically consistent with that of the uniform flow.
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