A low-speed compressor is designed for tip flow field of first stage rotor in the high-speed compressor with an inlet guide vane. It was prepared for subsequent experiments of the low-speed compressor stall and blade tip flow loss. The design used blade design and numerical simulation methods to ensure similar distribution of blade surface pressure coefficient and blade inlet and outlet main aerodynamic parameters of high- and low-speed compressors. High-speed prototype compressor was taken as research object to design a low-speed compressor. It included adjustment of flow-path geometry

iterative design of blade profiles and breakthrough the limitation of the geometric similar principle for inlet guide vane and first-stage rotor blade design. Finally

the comparative analyzed of geometry

aerodynamic parameters and flow-field structure of high- and low-speed compressor proved that the low-speed modeling design is useful. This design guarantees the similarity of processing capacity factor and rotor diffuser factor is 98.16%

94.95%

respectively

which is under the same flow coefficient.