摘要
通过引入非定常尾迹诱导过渡的时间平均间歇因子的概念，提出常规过渡的起始点位置和尾迹诱导过渡起始点位置的算法，实现了对非定常尾迹影响下涡轮叶片上时间平均换热的数值模拟。结果显示，无论在叶片吸力面还是压力面，计算与实验符合均很好。
The numerical simulation of influences of unsteady wake on the time average heat transfer of turbine blade was made by introducing the concept of wake induced transitional time averaged intermittency and putting forward methods for calculating both normal transition onset and wake induced transition onset. The agreement between predictions and experimental data is good both on suction surface and pressure surface of turbine blade.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第4期53-56,共4页
Journal of Propulsion Technology
基金
航空科学基金
关键词
航空发动机
涡轮叶片
传热
数值仿真
热效应
Aircraft engine,Turbine blade,Heat transfer,Numerical simulation,Thermal effect
