摘要
建立了包含高压涡轮(HPT)机匣基本结构在内的轴对称参数化模型,基于热固耦合变形和结构参数灵敏度分析结果,选择了灵敏度高的12个关键结构参数作为优化设计变量,采用第2代非劣排序遗传算法(NSGA-Ⅱ),开展了以机匣等效质量和挂钩处径向平均位移为目标函数的多目标优化。优化结果表明:机匣加强肋结构朝着有利换热的方向发展,其他结构朝着机匣质量减轻的方向发展;优化后模型质量及径向位移量均有所减小。
An axisymmetric parameterized high pressure turbine （HPT） casing model was established after HPT casing structure was analysed.Based on the thermal-structure coupling deformation and parameter sensitivity analysis result,12 key structure parameters were selected as optimization variables.Taking the casing mass and the hook area average radial displacement as the multi-objective function,the second generation non-dominated sorting genetic algorithm （NSGA-Ⅱ） was adopted to solve this multi-objective optimization problem.The optimization result showed that the optimal strengthening ribs structure was more efficient at heat conduction,and other optimal structure was more efficient at losing weight.After the optimization,the model weight and radial displacement were lessened simultaneously.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2017年第8期1992-1999,共8页
Journal of Aerospace Power
关键词
高压涡轮机匣
多目标优化
参数化模型
热固耦合
遗传算法
high pressure turbine casing
multi-objective optimization
parameterized model
thermal-structure coupling
genetic algorithm
