基于遗传算法的平板叶片阻尼识别  

Damping Identification of Plate Blade Based on Genetic Algorithm

作　　者：刘涛[1] 王加亮[1] 张帅 张霞妹 LIU Tao;WANG Jia-liang;ZHANG Shuai;ZHANG Xia-mei(Aero-Engine Station of Chinese Flight Test Establishment, Xi'anShaanxi 710089, China)

机构地区：[1]中国飞行试验研究院发动机所

出　　处：《机械研究与应用》2019年第3期8-11,16,共5页Mechanical Research & Application

摘　　要：航空发动机叶片的阻尼预测对叶片裂纹故障诊断、结构动力学分析等有重要的意义。通过平板叶片振动阻尼测量试验,获取不同平板叶片在不同冲量撞击作用下的振动响应信号,采用基于遗传算法的模型参数辨识方法对其响应信号进行辨识以获取其振动参数。分析结果表明,平板叶片的实测振动信号的振幅及衰减时间随撞击物的冲量变化而变化;对于小阻尼叶片,参数辨识法比一般方法计算的阻尼值更准确;同一叶片受不同冲量作用,其阻尼比保持不变;在相同冲量作用下,随着叶片结构尺寸变化,其阻尼比也相应改变。The damping prediction of aero-engine blades is important for blade crack fault diagnosis and structural dynamics analysis. Through the vibration measurement experiment of the plate blade, the vibration response signals of different plate blades under different impulses are obtained, and the response signal is identified by the model parameter identification method based on the genetic algorithm. The research indicates that the measured vibration signal of the plate blade under impact is complete and trend is correct. For small damper blades, the parameter identification method is more accurate than the damping value calculated by the general method. The blade is subjected to different impulses, and its damping remains unchanged;as the blade structure changes, its damping also changes accordingly.

关 键 词：平板叶片 阻尼 参数辨识 遗传算法 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]