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To improve the thrust-weight ratio of aero-engine and make it lightest, the weight reduction design method of a micro turbojet engine compressor is of a great importance. The finite element calculation is carried out on the solid compressor, and the stress and deformation data of the compressor structure under the condition of the design speed are obtained, which is used as the design constraint space for the weight reduction optimization. On this basis, the weight reduction optimization design of the solid part of centrifugal compressor disc is carried out with the help of the characteristics of high strength ratio and high material utilization factor of equal strength structure. Result shows that the weight reduction of the compressor can reach 20.3% under the condition that the equivalent stress of Mises is increased slightly and the radial displacement of the tip of the blade is not significantly changed compared with the load bearing capacity of the compressor before and after optimization.