Based on the mathematical model of continuum structure topology optimization

a 1/18 cyclic symmetric simplified fan structure model was established based on a gas turbine engine design. The topological optimization design of the structure based on solid isotropic material with penalization（SIMP） interpolation variable density method was proposed. In order to obtain a better topology optimization result of the fan disk structure

a method of combining the expanded optimization solution domain and the blisk structure was proposed

and with this method

three control groups were set correspondingly based on the design of the original fan disk. All simulation results were appropriately modified according to the actual structure and manufacturing process

and the dangerous working conditions were verified. Under the premise of meeting the performance requirements

the compressor quality was reduced by 349%.