航空发动机多辐板风扇盘拓扑优化与形状优化设计技术

Topology and Shape Optimization Method for Multi-Web Fan Disk in Aero-Engine

为了设计出高性能航空发动机风扇盘结构,首先采用基于自适应随机抽样双向渐进拓扑优化方法对风扇盘进行拓扑优化,得到轮盘合理拓扑构型,然后基于该拓扑构型,采用形状优化方法对轮盘构型做进一步优化。结果表明,在满足强度要求下,设计出了高性能的三辐板、四辐板风扇盘最终减重19.23%,21.59%(其中拓扑优化减重17.12%,19.43%),并且最优解应变能密度分布更加均匀,说明了宽弦风扇盘的合理构型是由若干辐板组成的多辐板结构。

In order to design a high-performance fan disk in aero-engine, the method called Bi-Direc- tional Evolutionary Structural Optimization based on Self-adaption and Random Sampling Strategy was used in the topologic optimization design of fan disks and obtained reasonable topologic configurations. Then, based on the topologic configurations,the shape optimization method was further adopted to design the struc- ture of fan disks. The results demonstrate that three-web and four-web fan disks are achieved whilst the strength requirements can be satisfied. The weight of the optimum fan disks is reduced by 19.23% and 21.59% respectively （the reduction of weight for two types of structures during the topology optimization is 17.12% and 19.43% , respectively）. Meanwhile the strain energy density is more uniform,which shows that the optimum structure of wide chord fan disks should be made up of several webs.