Single-stage centrifugal compressors are widely used in micro turbojet engine. In order to explore the design technology of high speed centrifugal compressor, a high speed centrifugal compressor with pressure ratio of 3.2 is designed using parameterization modeling method and summarized the key design method. The main design process was included of one-dimensional (1D) conceptual design to complete initial paratmetric selection, and based on two-dimensional (2D) through flow calculation, the aerodynamic design performance was obtained by finally using numercial simulation software analysis, through adjusting the distribution of velocity circulation to complete the three-dimensional (3D) modeling of blade rows. The results show that the performance and parameters of designed centrifugal compressor are reasonable in distribution for internal fluid working points, and can meet all the requirements in design.