摘要
本文用边界元法分析与计算了航空发动机涡轮工作叶片温度场的瞬态分布。
The boundary element method is applied to analyzing temperature field transient distribution on aeroengine turbine blades. It is possible to calculate the thermal stesses and life span of the blade and to check the blade strength according to the temperature field determined by this method. The temperature distributions on a set of different sections in a turbine blade at several instants have been calculated.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1989年第2期110-114,共5页
Journal of Aerospace Power
