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When an aircraft engine operates at a transonic regime, the Shock Wave Boundary Layer Interaction (SBLI) plays a significant role in aerodynamic performance and its effects are detrimental while operating at low Reynolds conditions. To investigate SBLI effects numerically and experimentally, a linear cascade 3-profile test section has been designed for the IMP-PAN transonic blow-down wind tunnel facility. A novel technique of inlet valves with perforated plates setup has been installed upstream of the test section to reduce the Reynolds number in the test section. Three different Reynolds cases ( \(7.4 \times 10^5\) , \(5.8 \times 10^5\) , and \(2.8 \times 10^5\) ) have been chosen for detailed flow structure comparison. The main focus of the research is on the suction side of the middle profile where the shock wave interacts with the boundary layer resulting in boundary layer separation. A detailed boundary layer investigation and the location of the separation bubble beneath the shock foot have been compared. The total pressure losses have been compared based on wake measurements downstream of the middle profile.

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Reynolds Number Effects on Shock Wave Boundary Layer Interaction in Highly Loaded Compressor Stator

  • 章节

  • 出版模式：

    开放获取

  • 发表日期：

    2025年

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  • Arun Joseph,
  • Pawel Flaszynski,
  • Michal Piotrowicz,
  • Piotr Doerffer,
  • Marcin Kurowski

摘要

When an aircraft engine operates at a transonic regime, the Shock Wave Boundary Layer Interaction (SBLI) plays a significant role in aerodynamic performance and its effects are detrimental while operating at low Reynolds conditions. To investigate SBLI effects numerically and experimentally, a linear cascade 3-profile test section has been designed for the IMP-PAN transonic blow-down wind tunnel facility. A novel technique of inlet valves with perforated plates setup has been installed upstream of the test section to reduce the Reynolds number in the test section. Three different Reynolds cases ( \(7.4 \times 10^5\) , \(5.8 \times 10^5\) , and \(2.8 \times 10^5\) ) have been chosen for detailed flow structure comparison. The main focus of the research is on the suction side of the middle profile where the shock wave interacts with the boundary layer resulting in boundary layer separation. A detailed boundary layer investigation and the location of the separation bubble beneath the shock foot have been compared. The total pressure losses have been compared based on wake measurements downstream of the middle profile.