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The aerodynamic performance of a compressor significantly depends on the Reynolds number (Re) condition at which the aircraft operates. In transonic regime Shock Wave Boundary Layer Interaction (SBLI) plays an important role on aerodynamic performance and its effects are detrimental when flying at low Reynolds conditions. To investigate SBLI effects numerically and experimentally a rectilinear 3-blade test section has been designed based on the streamlines extracted from cascade simulations. The main design criterion as an inlet Mach number of 0.9 has been defined by Rolls Royce Deutschland (RRD). Based on the requirements numerical investigations have been carried out on the test section with suction slots using the EARSM turbulence model with transition features included. The advantages of using the active flow control method in the test section have been defined in this paper. A detailed comparison of flow structure at different Reynolds conditions has been performed on the suction side of the middle profile in the test section.

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Investigation of Reynolds Number Effect on Shock Wave Boundary Layer Interaction on Compressor Stator Profile

  • 会议论文

  • 发表日期：

    2025年

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

摘要

The aerodynamic performance of a compressor significantly depends on the Reynolds number (Re) condition at which the aircraft operates. In transonic regime Shock Wave Boundary Layer Interaction (SBLI) plays an important role on aerodynamic performance and its effects are detrimental when flying at low Reynolds conditions. To investigate SBLI effects numerically and experimentally a rectilinear 3-blade test section has been designed based on the streamlines extracted from cascade simulations. The main design criterion as an inlet Mach number of 0.9 has been defined by Rolls Royce Deutschland (RRD). Based on the requirements numerical investigations have been carried out on the test section with suction slots using the EARSM turbulence model with transition features included. The advantages of using the active flow control method in the test section have been defined in this paper. A detailed comparison of flow structure at different Reynolds conditions has been performed on the suction side of the middle profile in the test section.