摘要
前缘逆主流喷射冷气对壁面静压有明显影响；冷气与主流掺混及卵型涡的形成导致近叶片表面处能量损失增加；吸力面或压力面根部出现与通道涡旋向相同或相反的涡系；卵型涡能够以一定形式保持到叶栅出口并与尾迹作用，使出口处气动参数剧烈变化．
The effects on the aerodynamic performance of turbine with cooling air injection fromleading edge were studied experimentally in a linear cascade rig. The results showed that thesurface pressure distribution was changed significantly by coolant injected from leading edge.The energy loss near the blade surface was increased and there was a little vortex which hasthe opposite or same sense of rotation as the passage vortex at the root of pressure or suctionsurface, this was due mainly to the mixing between the mainstream and the injecting air,and to the resultant formation of kidney--shaped vortex. The kidney--shaped vortex waskept near the blade surface at certain type, and mixed with the wake at the exit of thecascade.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
1999年第2期176-180,共5页
Journal of Engineering Thermophysics
基金
国家自然科学基金
哈工大校管航天基金
关键词
冷气喷射
气动性能
涡轮
叶栅
航空发动机
流场
cooling--air injection, aerodynamic performance, kidney--shaped vortex
