Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 13, 2020 - September 16, 2020
A large-scale Wall-Resolved LES (Large Eddy Simulation) has been conducted for a transonic axial compressor rotor, NASA Rotor 37. By using a very fine computational grid of 1.35 billion points for a single passage and a high resolution scheme based on a 6th-order compact interpolation, the fine vortex structure in the turbulent boundary layer was resolved, and the interference between the shock wave and the blade boundary layer, and the boundary layer separation due to the shock wave interaction were clearly captured. The total pressure distribution at the rotor exit (station4) in the LES results was in good agreement with that in the experimental results, and the pressure deficit on the hub side was well captured in the LES results. The total pressure on the shroud side was slightly overestimated in the LES results, which is due to an underestination of the tip leakage vortex and its associated flow loss.
