Based on the “General Theory of Three-Dimensional Flow in Turbomachines”, an improved method for designing centrifugal impeller blades has been developed. The design procedure is performed with the help of the combination of an S2 inverse problem code, a code for generating a profile on a revolution surface by a two-step series expansion and the codes of S1 direct and inverse problems. After the calculation of the inverse problem on the S2 stream surface is completed, a special series expansion method is used for obtaining a preliminary blade profile, then the relative flow field is predicted by the S1 direct code and is improved by the S1 inverse code. The method is favourable for smoothing the velocity distribution on the blade surface, eliminating the separation bubble and raising the efficiency of the impeller. The present method has been successfuly applied to improving the design of a centrifugal impeller.
An Improved Method for Aerodynamic Design of Centrifugal Impeller Blades
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Wang, Z, Wu, B, & Zhang, W. "An Improved Method for Aerodynamic Design of Centrifugal Impeller Blades." Proceedings of the ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. Volume 1: Turbomachinery. Orlando, Florida, USA. June 3–6, 1991. V001T01A024. ASME. https://doi.org/10.1115/91-GT-076
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