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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。
Proposed a new turbine disk structure optimization design, through the finite element method for aeroengine turbine disk structure optimization, and its intensity analysis and safety margin test to select the optimal structure. Based on the reference solid turbine disk, the structural topology of the cross section is optimized according to the lightest design principle to obtain a new hollow turbine disk. By judging whether the safety margin is within the permitted range, the hollow turbine The structural topology of the disk was modified to obtain a new type of hollow turbine disk. The structural strength of the standard solid disk disk and two new hollow disk disks were calculated and the safety margins were tested and compared. The calculation results show that: (1) The structural strength of the above three different types of turbine disks meets the design requirements given the same boundary conditions; (2) The safety factor of the lightest hollow turbine disks compared with the reference solid turbine disk (25.23%), which is beyond the scope of safety margin. (3) Compared with the lightest hollow turbine disk, the topologically modified hollow turbine disk has an increase of 1.08% in mass, but both the maximum equivalent stress and the maximum equivalent strain With a reduction of more than 10%, the safety margin meets the allowable requirements and is selected as the optimal structure. The optimization method has reference significance for the structural design of turbine disk.