Volume 35 Issue 6
Jun.  2020
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LIU Xiaogang, DAI Sicheng, WU Zhenhao. Topology optimization of gas turbine engine fan disk[J]. Journal of Aerospace Power, 2020, 35(6): 1121-1130. doi: 10.13224/j.cnki.jasp.2020.06.001
Citation: LIU Xiaogang, DAI Sicheng, WU Zhenhao. Topology optimization of gas turbine engine fan disk[J]. Journal of Aerospace Power, 2020, 35(6): 1121-1130. doi: 10.13224/j.cnki.jasp.2020.06.001

Topology optimization of gas turbine engine fan disk

doi: 10.13224/j.cnki.jasp.2020.06.001
  • Received Date: 2019-12-16
  • Publish Date: 2020-06-28
  • 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%.

     

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