Abstract
This aerodynamic study analyzes a novel design of centrifugal compressor impellers having double splitter blades for performance enhancement. It investigates the effects of the location of the splitter blades between two main blades. It is concluded that splitter blades have positive impacts on the compressor impeller performance once gas is compressed systematically with the alteration in location of splitters i.e., big or small splitters in cascade. Total pressure ratio is increased with improved efficiency in double splitter blade impellers. After a comprehensive comparison of location of the splitter blades in double splitter impellers i.e., big splitter blade and smaller splitter blade placement near to pressure surface or suction surface. It is identified that big splitter close to pressure surface and small splitter close to suction surface of main blade has uniform flow, reduced separation and better efficiency then placement of small splitter close to pressure surface.
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