Method and system for designing blade angle of gas compressor

The invention relates to the technical field of axial-flow, centrifugal and oblique-flow compressors, solves the problem of long consumed time period during design of blades of an existing compressor, and particularly relates to a method and a system for designing a blade angle of the compressor, and the method for designing the blade angle comprises the following steps: firstly, normalizing the chord length of each section blade profile of a blade into a closed interval [0, 1]; the relative position of the blade angle relative to the chord length of the blade profile is analyzed and recorded as x, and x belongs to [0, 1]; the method comprises the following steps: establishing a plurality of groups of polynomials to represent a blade angle distribution form, recording piecewise functions corresponding to the plurality of groups of polynomials in a closed interval [0, 1] as f (x), establishing a function program, introducing a group of sequences: Q, R, S and T, and analyzing and calculating the f (x); and adju