Dynamic finite element model validation of an assembled aero-engine casing

13th International Conference on Motion and Vibration Control; 12th International Conference on Recent Advances in Structural Dynamics

Huang, Zi^1,2 ; Zang, Chaoping^1,2 ; Jiang, Yuying^1,2 ; Wang, Xiaowei^1,2

Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing

210016, China^1

Collaborative Innovation Centre of Advanced Aero-Engine, China^2

关键词: Acceleration sensors;    Design and Development;    Dynamic characteristics;    Dynamic finite element model;    Dynamic model validation;    Eigen sensitivities;    Individual components;    Reliable connections;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/744/1/012139/pdf
DOI  :  10.1088/1742-6596/744/1/012139

来源: IOP

【 摘 要 】

Structural dynamic model updating and validation of an aero-engine casing is critical to the design and development of an aircraft engine. It helps to identify the dynamic characteristics and reduce the response of the aero-engine. The modelling and parameter identification of joint are extremely difficult and important in structural dynamic analysis of the assembled aero-engine casing. In this paper, dynamic model validation technique was applied to update and validate the finite element model of an assembled aero-engine casing. First, modal test of individual casings and the assembled casing was performed by using the traditional acceleration sensors and a hammer. The modal frequencies and mode shapes were obtained by modal analysis tools. Second, the Inverse Eigen-sensitivity Method was used to correct frequency errors and MAC values of correlated mode pairs in the individual components to obtain validated models. Last, the bolt joints of two aero-engine casings were modelled by thin layer of shell elements. The material parameters or element properties of the thin-layer contact elements were updated to obtain reliable connection parameters. The results show that the errors of natural frequencies between the validated FE model of an assembled aero-engine casing and test data are within 7%, and the MAC values of main modes are above 70%, which can verify the feasibility and effectiveness of this approach.