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

Dong Jiang, Huadong Li, Xiang Li, Yongbo Li, Yang Hu, Chang Liu, Chenghua Zhang and Yunfei Yan ()
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Dong Jiang: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
Huadong Li: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
Xiang Li: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
Yongbo Li: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
Yang Hu: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
Chang Liu: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
Chenghua Zhang: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China
Yunfei Yan: School of Energy and Power Engineering, Chongqing University, Chongqing 400044, China

Energies, 2025, vol. 18, issue 17, 1-23

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.

Keywords: segmented twisted stator blades; leading-edge baffles; flow deflection angle; combustor inlet simulator (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2025
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