基于流热固耦合的航空发动机涡轮叶片仿真分析

Simulation Analysis on Aero-engine Turbine Blades Based on Fluid-thermal-solid Coupling

为真实模拟某型民用航空发动机涡轮叶片的实际工作状况,需要同时考虑气动力、热应力、离心力三者共同作用,找出该型民用航空发动机涡轮叶片的疲劳危险部位。本文基于某型民用航空发动机实际快速存取记录器(QAR)飞行数据,利用ANSYS Workbench仿真软件对航空发动机涡轮叶片进行流热固耦合有限元仿真分析。结果表明,涡轮叶片等效应力和等效应变云图变化基本一致,最大应力和应变出现在涡轮叶片叶身与缘板交接处的前缘和后缘,最大应力和应变分别为4601.4MPa和0.026,且与其他部位数值相差较大,可将其列为疲劳危险部位,为后续研究涡轮叶片寿命预测分析和结构优化提供技术参考。

In order to realistically simulate the actual working conditions of the turbine blades of a certain type of civil aviation engine,the combined effects of aerodynamics,thermal stress and centrifugal force need to be considered to find out the fatigue hazard parts of the turbine blades of the civil aviation engine.This paper uses an ANSYS Workbench simulation software to conduct flow-thermal-solid coupling finite element simulation analysis on the turbine blades of the aviation engine based on the actual Quick Access Recorder(QAR)flight data of a certain type of civil aero engine.The results show that the equivalence force and the equivalence stress cloud map of the turbine blade are basically the same,the maximum stress and strain appear in the leading edge and trailing edge of the junction between the turbine blade body and the edge plate,and the maximum stress and strain is 4601.4MPa and 0.026,respectively,and the values of other parts are quite different,which can be listed as fatigue risk parts,which provides a technical reference for the subsequent study of turbine blade life prediction analysis and structure optimization.