Investigation of shockwave-turbulent boundary layer interaction in transonic compressor Rotor37

The internal flow dynamics within transonic compressors are characterized by a complex interplay of phenomena including shock waves, turbulent boundary layers, and vortices. Among these, the interaction be-tween shock waves and turbulent boundary layers (SWTBLI) stands out as a significant challenge in transonic compressor flow fields. This paper employs a high-precision Computational Fluid Dynamics (CFD) approach, utilizing the k-ω turbulence model, to analyze the flow behavior of Rotor37 within the transonic com-pressor. Specifically, we focus on studying the SWTBLI phenomenon within the rotor channels. The obtained results agree with the experimental values, and the total pressure ratio calculation error is less than 4%. Notably, due to the significant losses caused by shock waves, the adiabatic efficiency of Rotor 37 calculated is slightly lower than the experimental values. The calculation procedure developed in this paper can accurately predict the details of the shock wave/turbulent boundary layer interference in the rotor blade passages, which indicates that the CFD calculation procedure is suitable for flow calculation of transonic compressors.