航空发动机涡轮盘固有模态分析

Inherent Modal Analysis of Aero-Engine Turbine Disc

在动力分析中固有模态是非常重要的。固有模态分析的结果是多种动态行为的判据,也是进一步进行结构动力学分析的基础数据。应用ANSYS和振动实验两种方法,并以航空发动机的某级涡轮盘和损伤模型为例,进行涡轮盘约束情况下的固有模态计算,给出了两种方法的前3阶固有频率和振型。在对其进行分析后,得出ANSYS方法算出的结果与振动实验得出的结果基本相同,提出用ANSYS的结果代替振动实验结果,用以进行航空发动机零部件的仿真、损伤检测和优化设计等,解决工程中遇到的实际问题。

Inherent modal is of importance in dynamical analysis. The analytical result of inherent modal, which a criterion of the various dynamic action,is also the basic data carrying out the further analysis of structural dynamic. Applying two methods of ANSYS（analysis system） and vibration experiment,this dissertation takes the turbine disc of aero-engine and damage modals as examples to calculate the inherent modal under the circumstance which is in fully constrained state,then the first three inherent frequencies and vibration modes are shown. After the analyzing,it is proved that the two results calculated by ANSYS and vibration experiment separately are ahnost the same,and in order to make the simulation,damage detection and construction optimizaion design of aero-engine components, to resolve the actual problem during the project process,an opinion is given that it is necessry to substitute the result calculated by vibration experiment with that of ANSYS.