论文部分内容阅读
构件的疲劳寿命,在一般情况下是由裂纹形成循环数与裂纹扩展的循环数之和组成,在特殊情况下,可以重点确定其中一种。一、燃气涡轮构件材料高温高低循环复合疲劳寿命估算燃气涡轮盘、叶片等构件在其轮缘、孔边榫头及榫槽等局部关键部位,均承受着离心力和热应力的低循环载荷并叠加高循环振动载荷,简化载荷谱如本讲座(一)图4所示。失效寿命定义为控制应变的最大载荷下降25%所对应的循环块作为高低循环复合疲劳失效寿命,以下简称为高低循环复合疲劳寿命。
The fatigue life of a component, in general, consists of the sum of the number of cycles of crack formation and the number of cycles of crack propagation. In special cases, one can focus on one. First, gas turbine components at high temperature cycle composite fatigue life estimates Gas turbine disk, blades and other components in its rim, hole edge tenon and tongue and other key local parts, are subject to centrifugal force and thermal stress of low cyclic loading and stacking high Cyclic vibration load, simplified load spectrum as shown in this lecture (a) Figure 4. The failure life is defined as the cyclic load corresponding to a 25% decrease in the maximum load of the control strain, which is referred to as the high-low cycle compound fatigue life, hereinafter referred to as the high-low cycle compound fatigue life.