航空发动机叶片抗冲击动力学拓扑优化研究

本文运用了结合混合元胞自动机(Hybrid Cellular Automaton, HCA)方法和基于LS-DYNA显式有限元算法的动力学拓扑优化方法来解决非线性动力学拓扑优化问题，并形成了该方法迭代过程的数学模型．运用该方法，对某航空发动机叶片进行了动力学拓扑优化设计，给出了优化后结构的材料分布，并与优化前结构进行了对比分析．结果表明，优化后结构相比于优化前在材料分布上更加合理，在减少质量的同时降低了结构在冲击过程中的最大应力，实现了航空发动机的抗冲击优化，为航空发动机动态优化设计提供了有效分析方法．

Research on Topology Optimization with Dynamic Loads for Aero Engine Fan Blade

In this paper, the Hybrid Cellular Automaton (HCA) method combined with dynamic topology optimization method based on LS-DYNA explicit FEM were used to solve topology optimization problems of nonlinear dynamic systems. The mathematic algorithm of iteration process was also presented. This method was then applied to the dynamic topology optimization design of one aero engine fan blade. The material distribution of the optimized structure was given and compared with that of the initial structure. The results show that the optimized structure is more reasonable in terms of material distribution. Both the total mass and the maximum stress are reduced during the impact process, indicating that the objective of dynamic optimization design of aero engine fan blade for impact resistance is achieved. This method provides an effective approach for the dynamic topology optimization of aero engine fan blade.