摘要
从涡轮叶片典型部位取材并设计加工试件,进行持久寿命试验。通过观察比较试验结果,发现相同名义应力下气膜冷却孔将使试件的持久寿命大为降低。为了验证这一结论,采用有限元数值模拟的方法对该试件的持久拉伸过程进行模拟,同时考虑材料的正交各向异性以及高温条件下的蠕变规律,求得应力集中最大节点的应力值,进而算出其持久寿命,并与标准试件进行比较。
The endurance life experiments are made on the specimens cut from the typical part of the turbine blades with the film cooling holes （perpendicular-hole and nonperpendicular-hole）. The experimental results show that the film cooling holes have a significant influence on endurance life compared with standard specimens＇ one. To validate these results, FEA simulation is carried out using the orthogonal anisotropic property and creep law under high temperature. Moreover, the endurance life is obtained by computing the maximum stress value and its location and comparing with standard specimens＇ endurance life.
出处
《计算力学学报》
EI
CAS
CSCD
北大核心
2009年第3期437-441,共5页
Chinese Journal of Computational Mechanics
基金
航空科学基金(04C06002)资助项目
关键词
涡轮叶片
持久寿命
气膜冷却孔
数值模拟
turbine blade
endurance life
film cooling hole
numerical simulation
