某型发动机涡轮盘温度及应力计算分析

Temperature and Stress Analysis of Engine Turbine Disc

低循环疲劳是导致航空发动机涡轮盘失效的主要因素之一。以某型发动机的涡轮盘为研究对象,建立该涡轮盘的有限元模型并对其在最大工作状态下的温度和应力进行了分析计算,确定了涡轮盘热弹性应力和径向应力最大的1/4辐板处为低循环疲劳试验的考核部位,其工作温度为试验温度,为后续的低循环疲劳试验奠定了基础。

Low cycle fatigue（LCF）is one of the main factors leading to aero-engine turbine disc failure.The finite element model of a turbine disc was set up,its temperature and stress were calculated at the maximum working condition,and the LCF experiment was done.It was determined that the 1/4spoke of the turbine disc was one check point where the thermo-elastic stress and radial stress were maximum,and its working temperature could be used as the experiment temperature,which laid a good foundation for the subsequent LCF experiment.