非线性摩擦失谐叶片排序并行退火算法  

Mistuned blade arrangement with non-linear friction based on parallel annealing algorithm

作　　者：赵天宇[1] 袁惠群[2] 杨文军[1] 张宏远[1] 

机构地区：[1]东北大学机械工程与自动化学院,沈阳110819 [2]东北大学理学院,沈阳110819

出　　处：《航空动力学报》2016年第5期1053-1064,共12页Journal of Aerospace Power

基　　金：国家自然科学基金重点项目(51335003);国家自然科学基金(51275081);辽宁省科技创新重大专项课题(201303004);沈阳市科技计划高新技术产业发展与科技攻关计划项目(F13-01-21-00)

摘　　要：基于叶片模态实验获得的叶片失谐参数,基于非线性摩擦阻尼分析提出一种失谐叶盘结构的集中参数模型.综合模拟退火算法的局部搜索能力和遗传算法的全局搜索能力,并引入禁忌表作为搜索记忆表,提出了一种应用模拟退火进化算法附加禁忌表的叶片排序优化方法.同时结合图形处理器运算设计了基于compute unified device architecture(CUDA)的并行算法并且分析其算法性能.研究表明:基于并行框架寻优可以获得4.5倍的加速,同时按照优化后方案安装,可以明显降低叶盘系统振动响应幅值与方差.Based on mistuned blades parameters obtained by modal experiment,a lumped parameter model of mistuned bladed disk system was established considering the non- linear friction damping. Blade arrangement optimization method using simulated annealing evolutionary algorithm additional tabu list was proposed by combining the local search ability of simulated annealing algorithm and global searching ability of genetic algorithm. At the same time,a parallel algorithm was designed based on the computation unified device archi-tecture （CUDA） in combination with graphic processing unit. The results show that based on parallel framework optimization, the acceleration of 4.5 times can be obtained. Mean-while bladed disk system vibration response of the largest amplitude and variance can be sig-nificantly reduced when using optimized arrangement.

关 键 词：非线性摩擦 叶片排序 模拟退火算法 遗传算法 禁忌表 图形处理器 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]