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Simulation of Combustor Inlet Flow Field via Segmented Blade Twist and Leading-Edge Baffles

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  • Dong Jiang

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    AECC Sichuan Gas Turbine Estab, Mianyang 621000, China)

  • Huadong Li

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    AECC Sichuan Gas Turbine Estab, Mianyang 621000, China)

  • Xiang Li

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    AECC Sichuan Gas Turbine Estab, Mianyang 621000, China)

  • Yongbo Li

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    Key Laboratory of Low-Grade Energy Utilization Technologies and Systems, Chongqing University, Ministry of Education, Chongqing 400030, China)

  • Yang Hu

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    Key Laboratory of Low-Grade Energy Utilization Technologies and Systems, Chongqing University, Ministry of Education, Chongqing 400030, China)

  • Chang Liu

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    Key Laboratory of Low-Grade Energy Utilization Technologies and Systems, Chongqing University, Ministry of Education, Chongqing 400030, China)

  • Chenghua Zhang

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    Key Laboratory of Low-Grade Energy Utilization Technologies and Systems, Chongqing University, Ministry of Education, Chongqing 400030, China)

  • Yunfei Yan

    (School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
    Key Laboratory of Low-Grade Energy Utilization Technologies and Systems, Chongqing University, Ministry of Education, Chongqing 400030, China)

Abstract

High-fidelity replication of compressor exit flow fields is critical for combustor design, yet current simulation facilities lack effective, decoupled control of flow parameters. This study proposes a coordinated optimization strategy combining segmented stationary blade twist with leading-edge baffle configurations. The blades are divided into three spanwise sections with independently optimized twist angles to match airflow deflection. Upstream baffles are redesigned by reducing thickness, shortening horizontal length, and adjusting spanwise position to improve total velocity distribution. The final Plate-T configuration achieves a peak total velocity error of ~3.0% and position error of ~8.5%, while maintaining deflection angle accuracy. Experimental validation confirms improved agreement with compressor outlet flow fields, providing robust support for studies on flame stability, emissions, and combustion performance, as well as guidance for aero-engine experimental facility design.

Suggested Citation

  • Dong Jiang & Huadong Li & Xiang Li & Yongbo Li & Yang Hu & Chang Liu & Chenghua Zhang & Yunfei Yan, 2025. "Simulation of Combustor Inlet Flow Field via Segmented Blade Twist and Leading-Edge Baffles," Energies, MDPI, vol. 18(17), pages 1-23, August.
    • Handle: RePEc:gam:jeners:v:18:y:2025:i:17:p:4535-:d:1733668
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    References listed on IDEAS

    as
    1. Taimoor Asim & Dharminder Singh & M. Salman Siddiqui & Don McGlinchey, 2022. "Effect of Stator Blades on the Startup Dynamics of a Vertical Axis Wind Turbine," Energies, MDPI, vol. 15(21), pages 1-19, October.
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    3. Rahimi, H. & Schepers, J.G. & Shen, W.Z. & García, N. Ramos & Schneider, M.S. & Micallef, D. & Ferreira, C.J. Simao & Jost, E. & Klein, L. & Herráez, I., 2018. "Evaluation of different methods for determining the angle of attack on wind turbine blades with CFD results under axial inflow conditions," Renewable Energy, Elsevier, vol. 125(C), pages 866-876.
    4. Deng, Hangwen & Luo, Lei & Yan, Han & Zhou, Xun & Du, Wei & Luo, Qiao, 2025. "Experimental and numerical study on a three-stage high-load axial compressor with 3D blade design," Energy, Elsevier, vol. 316(C).
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