The catch of the laminar flow and the transition phenomenon in the compressor blade is the focus and key to study the laminar blade in compressor. The numerical simulation of a compressor blade is carried out by numerical method based on SST transition model. The numerical method based on SST transition model can accurately capture the laminar flow and transition phenomena of the blade surface which can not be captured by the ordinary turbulence model, and give the criterion for determining the transition of blade surface. On this basis, the influence of low Reynolds number environment and high turbulence environment on the laminar flow of the compressor blade surface is studied. It is verified that the laminar flow on the blade surface is possible under the actual compressor condition. The study provides numerical verification means and feasible verification foundation for the design of laminar blade in compressor in the flowing study.
Journal of Engineering Thermophysics
skin friction resistance
low reynolds number