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本文在增量——变刚度法的基础上,应用有限元素法,提出了一个求解航空发动机涡轮盘热弹塑性应力分析问题的方法和程序。用它可计算涡轮盘在弹性和弹塑性阶段的位移、应交和应力,以及涡轮盘的破裂转速和极限承载能力,还可以计算包含加载——卸载的过程,计算卸载后的残余变形和残余应力。大家知道,这对工程应用和结构的断裂力学分析尤其显得重要。值得指出,通过例题考核和某型航空发动机涡轮盘的实例计算,说明本文所用的方法在实践上是可行的,已为工程设计所采用。
Based on the incremental-variable stiffness method, this paper presents a method and procedure for solving the thermo-elasto-plastic stress analysis of aero-engine turbine disk using the finite element method. It can be used to calculate the displacements and stresses of turbine disks during the elastic and elasto-plastic phases, as well as the turbine disk rupture speed and ultimate load carrying capacity, as well as the process of loading-unloading, the residual deformation and residual after unloading stress. As you know, this is particularly important for fracture mechanics analysis of engineering applications and structures. It is worth pointing out that the method used in this paper is practically feasible and has been used in engineering design through example evaluation and example calculation of aeroengine turbine disk.