本文在正交异性材料定向结晶涡轮叶片的应力有限元分析的基础上，以一种简单的破坏模式列出了可靠度的计算方法。
This paper is based on stress analysis of directionally solidified turbine blade with the Finite Element Method. The reliability analysis method with a simple failure model is proposed.
本文利用大型非线性有限元通用程序对定向凝固结晶的气冷叶片进行了热弹性分析。
A general nonlinear finite element code has been applied to thermoelastic stress analysis of directionally solidified air cooled turbine blades.
利用高温云纹干涉法对航空发动机叶片定向结晶材料的高温蠕变进行了测试，获得该材料不同主方向的高温蠕变性质和规律。
The high temperature creep deformation of certain material used in aerial engines lamina was detected by means of high temperature moire interferometry in this paper.
结果表明，定向凝固合金叶片的断裂是由表面再结晶而导致的疲劳断裂失效。
The results show that the fracture on the superalloy blades resulted from the surface recrystallization on the blades.
结果表明，定向凝固合金叶片的断裂是由表面再结晶而导致的疲劳断裂失效。
The results show that the fracture on the superalloy blades resulted from the surface recrystallization on the blades.
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