抄録
The blade thickness of centrifugal impellers is relatively thin and the leading edge must be shaped into the arc or the ellipse with a small radius of curvature. As a consequence, it becomes difficult to generate the smooth computational grid without skewness in the process of CFD analysis. The modification of leading edge into the edge shape makes it possible to easily generate the computational grid with reduced skewness. However, the edge shaped leading edge may promote the leading edge separation and the development of boundary layer on the blade surface. In this study, the flow in three types of centrifugal compressor impeller which are different in the shape of blade leading edge was analyzed numerically. The computed results clarified the influences of the modification of blade leading edge shape on the flow behavior in the impeller passage and the aerodynamic performance of impeller.
