The multidisciplinary design optimization method of aero engine fan blade based on the airworthiness compliance and approximation model

摘要

Purpose - The purpose of this paper is to introduce the multidisciplinary design optimization method using approximation model for the aircraft engine fan blade based on the airworthiness compliance such as stress, vibration, and bird impact. Design/methodology/approach - Firstly, the airworthiness analysis of the typical fan blade was carried out based on the numerical simulation. Secondly, the design of experiment (DOE) was utilized to construct the approximation model of the fan blade. Finally, the airworthiness optimization of fan blade was carried out based on Kriging approximation model. Findings - The numerical simulation result shows that the analysis method can show the airworthiness compliance in the design stage. And the optimization result shows that structure, bird impact and vibration characteristics improve obviously, satisfying the constraints conditions of optimization. Originality/value - The multidisciplinary design optimization method of fan blade based on the airworthiness and approximation model is presented and achieved.