航空发动机涡轮盘结构优化设计  

Optimization design for the turbine disk of a gas engine

作　　者：王营[1] 余朝蓬[1] 

机构地区：[1]北京青云航空仪表有限公司,北京100086

出　　处：《机械设计与制造》2010年第5期4-6,共3页Machinery Design & Manufacture

基　　金：新世纪优秀人才支持计划资助(NCET-05-0189)

摘　　要：提出一种新的涡轮盘结构优化设计方案,通过有限元方法对某航空发动机涡轮盘进行了结构优化,并对其进行强度分析和安全裕度检验以选取最优结构。在基准实心涡轮盘的基础上,按照质量最轻的设计原则对其截面进行了结构拓扑优化,得到一种新的空心涡轮盘;通过判断其安全裕度是否在许用范围,对该空心涡轮盘进行结构拓扑修正,得到另外一种新的空心涡轮盘,对基准实心涡轮盘与两种新的空心涡轮盘的结构强度进行了计算和安全裕度检验以及对比分析。计算结果表明:(1)在给定相同边界条件下,上述三种不同结构涡轮盘的结构强度均满足设计要求;(2)与基准实心涡轮盘相比,质量最轻的空心涡轮盘安全系数降低了25.23%,超出了安全裕度范围;(3)拓扑修正后的空心涡轮盘与质量最轻的空心涡轮盘相比,质量增加了1.08%,但最大等效应力和最大等效应变均有超过10%的降低幅度,安全裕度符合许用要求,选为最优结构。该优化方法对涡轮盘的结构设计具有借鉴意义。A new optimization process is conducted for the turbine disk of a gas engine by using the finite element analysis（FEA）method,the optimal turbine disk is selected through analyzing the intensity and testing the safety margin of the original and the optimized turbine disks.One hollow turbine disk is obtained through optimizing the section of the standard solid turbine disk by using minimum weight criterion;the other hollow disk is obtained by using structure topological correction on the previous optimized hollow disk through inspecting the safety margin.The intensity and the safety margin include comparison of the original and the two new optimal hollow turbine disks are analyzed by using the numerical simula tion method.As a result,the intensity of three different kinds of turbine disks all meets the design intensity requirements,and the safety factor of the minimum weight hollow disk is decreased 25.23% than the original and exceed the safety margin.The weight of corrected hollow turbine disk is increased 1.08% and the Von Mises stress and Von Mises total strain is decreased more than 10% by comparing the minimum weight hollow disk,the corrected hollow turbine disk is selected as the optimal turbine disk for the gas engine for its satisfying the safety margin.The approach can be applied to the structure design of the gas engine disk.

关 键 词：有限元方法 涡轮盘 结构优化 安全裕度 拓扑修正 

分 类 号：TH12[机械工程—机械设计及理论] V232.3[航空宇航科学与技术—航空宇航推进理论与工程]