Geometric Error Analysis of Compressor Blade Based on Reconstructing Leading and Trailing Edges Smoothly

In the process of blade design, the shape of blade, which causes great influence on aerodynamic performance, is the most difficult part for designer. The shape of blade changes because of the cutting force, residual stress and deformation. To analyze the precise error of this, this paper presents a new algorithm for reconstructing cross section curve of blade from measuring points. The Gauss-Newton method and dichotomy are used to fit the circle of leading and trailing edge, which is the most important part of blade. Then the deformation error, contour error and parameter error are calculated with relative algorithm based on the new cross section curve. Also, a series of points and a blade model are utilized to demonstrate the effectiveness of this novel algorithm on reconstructing cross section curve and analyzing machining error.