Hybrid RANS-LES Versus URANS Simulations of a Simplified Compressor Blades Cascade
Based on a previous experience from BR710 and BR725 Roll-Royce fan blade development programs, the phenomena of shock wave-boundary layer interaction (SWBLI) are known to be of critical importance regarding engine safety and performance. In the European TFAST Project (Transition Location Effect on Shock Wave Boundary Layer Interaction), experiments and numerical simulations of unsteady and transitional SWBLI phenomena in a simplified compressor blades cascade are performed. Two blades of 100 mm are set-up in a 100*100 mm channel. The grid used is 9,6 M cells with \(y^+<1\) everywhere. The inlet turbulence intensity is set to 4 % and the Mach number has been adjusted to be 1.22 in front of the lower blade. In the present paper, unsteady transitional RANS and hybrid RANS-LES computations of the flow around two compressor blades are performed with the NSMB solver. Simulations with Spalart-Allmaras and \(k-\omega \) turbulence models in their URANS and DDES formulation as well as \(k-\omega \) SAS are performed.
KeywordsMach Number Lift Coefficient Compressor Blade Boundary Layer Interaction Transonic Compressor
This work has been carried out in the context of the European project TFAST. We acknowledge the CPU allocation on the French Supercomputing Centres IDRIS and CINES.
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