| Citation: | MIAO Huihui, ZHANG Zhaobo, WANG Yi, et al. Study on evolution mechanism and performance impact of swirl distortion in intake system of TBCC engine[J]. Journal of Aerospace Power, 2026, 41（10）：20250357 doi: 10.13224/j.cnki.jasp.20250357
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To investigate the generation law of swirl distortion in a turbine combined engine and its influence on the performance of axial flow compressors, an integrated model of a supersonic inlet S-bend diffuser section and axial flow compressor rotor was constructed to carry out numerical simulation calculations under a typical operating condition. The generation mechanism and law of swirl distortion were analyzed in detail, and the influence of swirl distortion on the performance of the compressor system was studied. The results indicated that the back pressure at the outlet of the supersonic S-bend inlet influenced the terminal shock wave position, thereby changing the energy distribution of the airflow in the diffuser section and consequently affecting the type and intensity of swirl distortion. Specifically, a strong paired swirl formed at low back pressure; the flow became nearly uniform with very weak swirl at medium back pressure; and a strong bulk swirl was generated at high back pressure. For system-level calculations under high-altitude uniform inflow conditions, the average static pressure at the aerodynamic interface plane remained below the inlet’s critical back pressure at 80%, 90%, and 100% compressor speeds across various outlet static pressures. This indicated that the inlet operated in a supercritical state, resulting in a symmetric energy distribution at the S-bend diffuser inlet and the formation of a paired swirl downstream. Under the above system-level calculation conditions, the compressor exhibited a narrowed operating flow range across all rotational speeds, along with reductions in both pressure ratio and efficiency at identical operating points, compared with its isolated component performance. Specifically, the maximum efficiency of the compressor rotor decreased by 5.49%, the flow rate at the maximum efficiency point decreased by 8.82%, and the stability margin decreased by 57.82%.
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