摘要
提出了一种基于遗传优化理论的涡轮增压器叶轮的优化设计方法,论述了以涡轮增压器叶轮能量损失最小为目标函数,以叶轮叶片进口角、进口直径、进口宽度、出口直径、叶片数、出口角为设计变量的涡轮增压器叶轮的优化设计模型及优化计算的方法,数值计算表明,这种算法可以方便地求得具有最小涡轮损失的涡轮叶形参数.
Based on genetic optimization theory, in this paper offers an optimal design method for the blade of turbocharger. This optimal method takes the minimal energy loss of the impeller as its objective function f (x). Design variables are vanes intake angle (bb1), vanes intake diameter (D1), vanes intake width (b1), vanes outlet diameter (D2), vanes number (z), vanes outlet angle (bb2). The purpose is to search for the optimal blade profile by genetic algorithm (GA) process, and finally to generate an optimal design. The numerical calculations show that the ap- proach successfully worked out the profile parameters of blade that has minimal losses.
出处
《装甲兵工程学院学报》
2001年第3期71-76,共6页
Journal of Academy of Armored Force Engineering
关键词
遗传算法
优化设计
增压器
叶片
genetic algorithm
optimization
turbocharger
blade
