基于遗传算法的榫槽部位模拟件设计方法  

Design Method of Simulation Specimen of Disc Slot Based on Genetic Algorithm

作　　者：艾兴 叶璇 李坚 张志佾 王佰智 张峻峰 AI Xing;YE Xuan;LI Jian;ZHANG Zhi-yi;WANG Bai-zhi;ZHANG Jun-feng(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou Hunan 412002,China;AECC Aero Engine Academy of China,Beijing 101304,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中国航空发动机研究院,北京101304

出　　处：《航空发动机》2022年第5期111-115,共5页Aeroengine

基　　金：湖南省自然科学基金(2019JJ50700);国家科技重大专项(2017-I-0006-0007、J2019-IV-0008-0076);中国航发创新基金(CXPT-2019-002)资助。

摘　　要：航空发动机构件的模拟件设计方法已成为工程领域研究的重要内容。设计出能反映实际构件真实服役状态的模拟件,可节约试验成本和周期,对构件有效地完成试验考核具有重要意义。针对航空发动机榫槽部位应力分布情况,将遗传优化算法与商用有限元软件ABAQUS相结合,提出航空发动机榫头/榫槽特征部位模拟件设计方法。利用该方法实现自动搜索榫头/榫槽特征部位处第1主应力最大梯度路径,并获取该路径上的应力分布。结果表明:该方法设计的模拟件最危险点的应力状态与零部件特征部位处的应力状态保持一致,二者在最危险点附近一定区域内应力梯度相同;所设计的模拟件与零部件的应力状态吻合较好,可以模拟任意情形下的应力及应力梯度。The design method of simulation specimen has become an important part in the field of engineering research.It is of great significance to design the simulation specimen which reflects the real service status of the actual components for the effective completion of the test and assessment of the components.A design method of aeroengine blade root/disc slot simulation specimen was proposed by combining genetic optimization algorithm and commercial finite element software ABAQUS for stress distribution of aeroengine disc slot.This method can automatically search the path of the maximum gradient of the first principal stress on the blade root/disc slot specimen,and obtain the stress distribution on the path.The results show that the stress state of the most dangerous point of the simulated specimen designed by this method is consistent with the stress state of the corresponding feature of the component,and the stress gradients of the two parts in the vicinity near the most dangerous point is the same.The stress state of the designed simulation specimen is in good agreement with that of the simulated component,and the stress and stress gradient can be simulated under any circumstances.

关 键 词：榫头/榫槽 模拟件 遗传算法 应力 航空发动机 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]