Due to the different curvature characteristics of different forms of parametric curves, the constructed two-dimensional compressor blade geometries are different, which affect the aerodynamic performance of the compressor blades. In this paper, MAN GHH 1-S1 blade profile is selected as the baseline. The redesign cascades are constructed from the camber line using Bezier curve, polynomial curve and the curvature integral curve respectively. Numerical simulations are calculated to discuss the influence of the parameterized curve of the camber line on the performance of the cascades. The research results show that the modified cascade of curvature integration method can effectively reduce the profile loss at various incidences and widen the incidence angle range.