An Improved Method for Aerodynamic Design of Centrifugal Impeller Blades

Abstract

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.

Advances in research on inverse and hybrid problems of turbomachinery aerothermodynamics in China

“…[38] by incorporating a boundary layer solver of integral type. Based on this method, Wang et al proposed a quasi-3-D design procedure for impellers [39,40].…”

Numerical Study on Vortical Flow Structure and Performance Enhancement of Centrifugal Compressor Impeller

“…The flow phenomena occurring in the centrifugal compressor are largely influenced by the shape of the impeller and the flow passage between the hub and the shroud [15]. Several methods are used for designing the geometry of flow passage and the impeller blades [15][16][17], however, the configuration of the air compressor is largely determined by the designer's experience and intuition [12]. Therefore, the manufacturer's design is usually modified (enhanced) to improve the performance based on the flow structures within the passage after CFD calculations.…”