摘要
根据小尺寸涡轮叶片的前缘特征,设计了U型通道冷却结构,在通道前缘设计了3种不同偏置方向的旋流冲击孔,改变了旋流方向,数值模拟研究了其对叶片前缘冷却效果的影响。结果表明:采用旋流冲击冷却结构时,冷却气附壁性增强,叶片前缘冷却效果相比常规冲击冷却明显提高;采用冲击孔向偏吸力面设置,利用了吸力面的低压特点,冲击流速提高,使压力面与吸力面冷却效果均有增强;获得了燃气与冷却气沿程压力与温度变化,为冷却气流路优化设计与流量分配提供了基础。
The cooling characteristics of turbine blade leading edge with swirling impinging structure were numerically investigated. The impact of impinging hole structure bias direction of blade leading edge was analyzed. The results show： when blade leading edge is designed for vortex impact,the cooling effect is improved than conventional cooling structure; whenthe slant hole vortex impact structure was in the suction side,the cooling effect was stronger than that caused by slant holevorteximpact structurein pressure surface; the distribution of gas and cooling gas pressure and temperature were revealed,which formed the effective basis ofoptimizing of design and the flow distribution of cooling air.
出处
《重庆理工大学学报（自然科学）》
CAS
2016年第11期49-55,120,共8页
Journal of Chongqing University of Technology：Natural Science
关键词
小尺寸涡轮叶片
叶片前缘
旋流冲击
偏置方向
流量分配
small turbine blade
leading edge
swirling
impinging cooling
offset direction
flow distribution
