Optimal Design Of Compressor Blade Profile And Aspirated Hole

This paper has simulated the flow field of aspirated compressor blade with method of numerical calculation, and analyse the effect of boundary layer aspiration on the flow field of subsonic compressor cascade. With method of numerical aerodynamic shape optimization of CFD, we try to add aspirated hole as a design variable to automatic optimization of turbomachinery blade, hope to develop ability of blade and explore a effective method to improve flow, with which we can design higher performance turbomachinery blade.We use N-S equation to calculate flow field of compressor blade cascade; choose B-L model as turbulent model; plot the computation area with H grid.The results show that boundary layer aspiration can effectively improve aerodynamic performances of cascade, reduce flow loss and increase blade load; with certain aspirated flow mass, along blade surface we can find the best aspirated location make cascade loss minimum; for compressor cascade with large camber angle with flow separation, proper aspirated location will effectively control development of boundary layer and eliminate separation, enhance aerodynamic performances of the compressor cascade.With the followed optimization, this paper also investigates the influences to the performance of compressor blade cascade by numerical aerodynamic optimization, and the performances of final cascades are further improved and reach higher level. This result shows that the optimization system designed in the paper is really reasonable and effective.