基于FE-ERSM航空发动机叶盘结构可靠性研究

Reliable Research of the Bladed Disk Assemblies of Aeroengine Based on FE-ERSM

为了更准确地描述航空发动机叶盘结构的变形以及控制的合理性,提出了一种高效高精度的概率分析方法,即有限元-极值响应面法(finite element-extremum response surface method,简称FE-ERSM)。该方法与响应面法(response surface method,简称RSM)和蒙特卡罗法(Monte Carlo method,简称MCM)相比,在不降低精度的情况下,效率显著提高,具有非常重要的工程应用价值。在分析中考虑了典型载荷,选取输入变量且考虑了参数的不确定性等因素。通过概率分析,不仅获得了其径向变形可靠度和径向变形以及应力场模拟样本、极值响应面、相对概率分布,而且对其径向变形和应力场进行灵敏度分析,得到了影响叶盘结构径向变形以及应力场分布的主要影响因素。最后,将FE-ERSM与RSM和MCM比较分析,验证了该方法在航空发动机叶盘结构分析中的合理性。

In order to more precisely describe the bladed disk assemblies deformation and the control of the aero-engine,a highly accurate and efficient method of probability analysis called finite element-extremum response surface method(FE-ERSM)is proposed,based on previously determined results.Compared with the response surface method(RSM)and Monte Carlo method(MCM),it significantly improves efficiency without reducing accuracy and has high value in important engineering applications.This paper considers many key indeterminate factors for modeling and analysis,such as the dynamic feature of the temperature load,the centrifugal force,and the boundary conditions.The radial deformation reliability,radial deformation displacement,historical sample,extreme response surface,relative probability distribution of its stress and radial deformation,and sensitivity of the stress distribution are obtained.The main factors affecting bladed disk assemblies deformation and stress distribution are investigated via the model′s sensitivity analysis.Finally,compared with the RSM and MCM approach,the results show that this new approach is more efficient and reasonable in its calculations.