A preliminary design method for turbomachinery blade rows using Clebsch formulation

摘要

A preliminary design method for turbomachinery blade rows in compressible flow is presented. Clebsch formulation of steady rotational flow and continuity equation are used to determine the flow field. The flow parameters are divided into circumferentially averaged and periodic terms. The blade shape is computed iteratively by modifying the geometry to satisfy local tangent velocity condition. The method are applied to different type of blade rows with different inlet mach numbers, the results demonstrate the robustness of the method.