摘要
安装航空发动机转子叶片时,由于制造误差使各叶片间存在失谐,不同的叶片安装方案影响叶片轮盘系统强迫振动响应的大小。通过叶片模态试验获得叶片失谐频差,进而获得叶片失谐参数,建立了失谐叶轮盘系统单个扇区两自由度集中参数动力学模型。基于遗传算法的全局优化和快速收敛性,利用改进的嵌套遗传算法给出某型航空发动机某级叶片轮盘系统叶片的最佳安装方案,按该方案安装叶片,可使发动机叶片轮盘系统强迫振动响应的最大幅值达到最小或处于较小的范围内。
In the process of installating aero-engine rotor blade,the manufacturing errors of blades can lead to the mistuned effects among the blades.Different assembly plans of blades produce different forced vibration responses of the bladed-disk system.It can obtain mistuned frequency difference of blades by a modal test,and then get the mistuned parameters.A 2-DOFs lumped-parameter kinetic model of single sector is built in a mistuned bladed-disk system.Based on the advantage of overall optimization and fast convergence of genetic algorithm,and using the improved nested genetic algorithm,a blade′s optimization assembly scheme of a certain bladed-disk system is proposed for a certain type aero-engine.The scheme can make the maximum amplitude of forced vibration response achieve minimum one or in a smaller range.
出处
《振动．测试与诊断》
EI
CSCD
北大核心
2011年第5期647-651,668-669,共5页
Journal of Vibration,Measurement & Diagnosis
基金
国家自然科学基金资助项目(编号:51175070)
沈阳市科学技术计划资助项目(编号:F10-205-1-35)
