Centrifuge impeller is a key component in micro aviation gas turbine. It is required to reduce the weight of the structure as much as possible on the premise of satisfying the aerodynamic performance. Traditional design and manufacturing technology has been basically played to the extreme, but the development of additive manufacturing technology and topology optimization design method has expanded new space for its further optimization design. In order to solve the weight reduction design problem of centrifugal impeller of a certain aviation micro gas turbine, based on additive manufacturing and topology optimization design technology, the static strength analysis of the centrifugal impeller is carried out first, and then the centrifugal impeller topology optimization based on the skeleton model and achievable process design is developed. And finally check the optimized model. The optimized design results show that the optimized design scheme can reduce the weight of the centrifugal impeller by 8.7%, and the power-gain ratio of the micro-gas turbine can be further improved.At the same time, the maximum deformation is reduced by 7.5%.The maximum equivalent stress is reduced by 0.59%, which improves the safety margin of centrifugal impeller when working.The optimized effect is obvious and the manufacturing process is feasible.