摘要
在连续体结构拓扑优化数学模型的基础上,根据某燃气涡轮发动机设计图建立了1/18循环对称简化的风扇结构模型,基于固体各向同性材料惩罚(SIMP)模型插值的变密度法对结构进行了拓扑优化设计。为了获得更好的风扇盘结构拓扑优化结果,提出了一种将增加质量和整体叶盘结构相结合的方案,并应用该方案,在原始风扇盘模型的基础上设计了三种扩大求解域后的对照模型。对所有的优化结果进行模型重建,并对危险工作条件进行了校核验证。结果表明:采用该方法对某型发动机风扇盘进行结构拓扑优化,能在满足强度和刚度要求的前提下使压气机质量减少34.9%。
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%.
作者
刘小刚
戴思成
吴振豪
许磊
申顺
LIU Xiaogang;DAI Sicheng;WU Zhenhao;XU Lei;SHEN Shun(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第6期1121-1130,共10页
Journal of Aerospace Power
基金
国家科技重大专项(2017-Ⅳ-0012-0049)
中央高校基本科研业务(NS2016022)。
