摘要
在低雷诺数 Ｋε双方程紊流模型程序基础上，通过引进一种离散孔气膜冷却的喷射模型，预测了涡轮叶片上有冷气出流情况下的冷却效率，包括对不同吹风比， 不同二次流与主流的密度比，不同主流紊流度，不同展向孔间距，单排孔不同孔排位置及多排孔同时有冷气出流等多种情况，总结出了喷射模型中两个重要参数的变化规律，计算结果与实验数据符合程度良好。
Predictions of spanwise averaged effectiveness are presently made on the basis of a two dimensional injection model for the discrete hole injection process that is incorporated in a two dimensional boundary layer code using the low Reynolds number K ε two equation turbulent model. Attention is given to the cases of turbine blade with film cooling both on suction surface and pressure surface, including the influence of blowing rate, density ratio, turbulence intensity, ratio of hole space to hole diameter, location of single row and multi row. Two constants, entrainment fraction and aerodynamic drag coefficient used in the injection model, are modified for these cases. The agreement between predictions and experimental data are good.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1999年第5期416-420,共5页
Acta Aeronautica et Astronautica Sinica
