鸟撞工况下HCA动态拓扑优化整级叶片的数值模拟

A Numerical Simulation of HCA Dynamic Topology Optimization Design of Whole Blade under Bird Strike

航空领域中飞机发动机在满足抗鸟撞性能的前提下,实现轻量化是关键问题之一。针对航空发动机冷端风扇叶片,基于HCA算法的动态拓扑优化方法对叶片实现进一步减重,为了验证该动态优化方法的有效性,建立了鸟撞航空发动机整级叶片冲击动力学有限元模型,模拟受气动与离心载荷作用下高速稳定旋转的发动机风扇叶片遭受鸟体撞击的瞬态响应过程。基于LS-DYNA软件平台,对考虑了鸟撞的多工况、多约束条件下叶片的动态优化结果与优化前叶片的多项动态响应指标进行了对比分析,证明了HCA动态拓扑优化方法比传统叶片轻量化方法更为优秀,在满足适航条例强度要求的同时可使叶片减重比达到37.9%,论证了在叶片轻量化设计上基于HCA算法的动态拓扑优化方法的可行性与优越性。

It is always an important issue to improve the light-weight design of aero-engine fan blades in aviation industry,while guaranteeing these blades high level of bird impact resistance. A better distribution of materials in the design of the fan blade was obtained on the basis of the hybrid cellular automaton(HCA)topology optimization method. This method covers multi-constrained conditions and multi-case impacting loads for aeroengine blades under bird strike. The applicability and feasibility of the optimization method was verified according to the simulation of full scale bird impact on the rotating optimized whole blades on LS-DYNA software platform. The finite element model of the optimized whole blade and SPH model of the bird were both established in the simulation. The results of the optimized whole blade of various dynamic responses for bird impact upon different parts proved that the topology optimization using hybrid cellular automaton algorithm for aero-engine fan blades is efficient and practicable. The results showed that it could acquire about 37.9% weight reduction of the aero-engine blade,which is much better than traditional optimization methods.