摘要
1 引言 现代航空发动机的燃气温度愈来愈高,涡轮叶片采用复杂的冷却结构和耐高温的各向异性材料。在发动机工作状态循环变化中,将引起热疲劳损伤。所以,必须对涡轮叶片中周期性变化的热应力进行分析。由于其结构形状复杂,采用有限元素法进行分析是一种有效的方法。如对整个叶片进行瞬态温度场和各个瞬间的应力场进行分析。
A method suitable for engineering calculation of thermal stress with plane-end boundary condition was presented.The turbine cooling-blade is made from orient clotting high-temperature alloy. The computation based on a tiny part from a blade allows for the influence of temperature on material properties. Finally, the calculation of transient temperature, thermal stress of some engine turbine cooling bladees are carried out during one thermal cycle test.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1991年第7期A428-A430,共3页
Acta Aeronautica et Astronautica Sinica
关键词
航空发动机
高温合金
叶片
热应力
turbine cooling blade, thermal stress analysis, high-temperature alloy.
