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<p>To mitigate the aerodynamic losses induced by corner separation in high-load compressors, this study investigates a representative high-load compressor cascade. A combined approach of numerical simulation and multi-objective optimization is employed to explore the synergistic control mechanism between endwall jet and blade curvature. Results indicate that the coupled configuration of a near-leading-edge endwall jet and a mildly backward-curved blade yields the most favorable control performance. Under the design condition, the loss coefficient exhibits a slight reduction, whereas under the near-stall condition, the total pressure loss coefficient decreases from 0.1799 for the baseline to 0.1611, corresponding to a 10.45% reduction. Moreover, the stable operating range of the cascade is considerably extended. The synergistic control mechanism can be attributed to two complementary effects. First, the mild backward curvature of the blade establishes a radial pressure gradient directed from the midspan toward the endwall. This gradient not only reduces flow losses in the midspan region but also drives low-energy fluid toward the endwall, thereby optimizing the jet impact region. Second, the endwall jet injects high-energy fluid into the boundary layer, enhancing the mixing between the main flow and the boundary layer. This suppresses the accumulation of low-energy fluid and restrains the development of passage and corner separation vortices, effectively delaying the onset of flow separation. SHAP-based sensitivity analysis reveals that the jet axial position, jet angle, and jet mass flow rate are the dominant parameters governing loss characteristics under both operating conditions. These parameters exhibit distinct operating-condition dependence and strong interaction effects, particularly near the stall point. The present study confirms the engineering feasibility of the synergistic control strategy combining endwall jet and mild blade curvature, providing a practical and theoretically grounded pathway for aerodynamic optimization of high-load compressor cascades.</p>

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Investigation of the Coupled Control Between Endwall Jet and Blade Curvature in a Compressor Cascade

  • 期刊论文

  • 发表日期：

    2025年10月30日

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  • Jiafu Chen,
  • Wuli Chu,
  • Yihao Shen,
  • Yafei Qiao,
  • Zezhen Sun

摘要

To mitigate the aerodynamic losses induced by corner separation in high-load compressors, this study investigates a representative high-load compressor cascade. A combined approach of numerical simulation and multi-objective optimization is employed to explore the synergistic control mechanism between endwall jet and blade curvature. Results indicate that the coupled configuration of a near-leading-edge endwall jet and a mildly backward-curved blade yields the most favorable control performance. Under the design condition, the loss coefficient exhibits a slight reduction, whereas under the near-stall condition, the total pressure loss coefficient decreases from 0.1799 for the baseline to 0.1611, corresponding to a 10.45% reduction. Moreover, the stable operating range of the cascade is considerably extended. The synergistic control mechanism can be attributed to two complementary effects. First, the mild backward curvature of the blade establishes a radial pressure gradient directed from the midspan toward the endwall. This gradient not only reduces flow losses in the midspan region but also drives low-energy fluid toward the endwall, thereby optimizing the jet impact region. Second, the endwall jet injects high-energy fluid into the boundary layer, enhancing the mixing between the main flow and the boundary layer. This suppresses the accumulation of low-energy fluid and restrains the development of passage and corner separation vortices, effectively delaying the onset of flow separation. SHAP-based sensitivity analysis reveals that the jet axial position, jet angle, and jet mass flow rate are the dominant parameters governing loss characteristics under both operating conditions. These parameters exhibit distinct operating-condition dependence and strong interaction effects, particularly near the stall point. The present study confirms the engineering feasibility of the synergistic control strategy combining endwall jet and mild blade curvature, providing a practical and theoretically grounded pathway for aerodynamic optimization of high-load compressor cascades.