[关键词]
[摘要]
为分析冷气掺混对涡轮叶栅气动性能的影响,对某船用燃气轮机高压涡轮导叶开展了带冷气条件下的扇形叶栅吹风试验,结果表明:冷气掺混对叶片型面压力分布有较大影响,且在吸力面表现尤为突出;在冷气流量比小于7%工况下,叶栅能量损失较无冷气喷射时增加(< 9%),甚至在Ma=1.05时能量损失较无冷气喷射时还小;当冷气流量比大于7%时,叶栅能量损失随冷气流量比的增大而迅速增加(最大可达26%);平均出口气流角随着出口马赫数的增加而增大,变化范围为17.7°~18.1°,且在同一工况下冷气喷射会使平均出口气流角增大。
[Key word]
[Abstract]
To study the influence of cooling-air ejection on the aerodynamic performance,in the paper,an experimental investigation of a turbine sector cascade with a series of cooling-air holes at different position of blade surface was carried out,and the effects of cooling mass flow rate on aerodynamic parameters under different outlet Mach number were compared and analyzed.Results showed that the cooling-air injection evidently influences the pressure distribution on the blade,especially on the suction side.Secondly,the energy loss increase is less than 9% compared to the case without cooling-air,and even less underMa=1.05 when the cooling-air flow ratio is under 7%.However,the energy loss is increasing quickly with the cooling-air flow ratio above 7%,and can reach the maximum of 26%.Lastly,the flow angle of outlet increases with Mach number of outlet,in range of 17.7°~18.1°,and the cooling-air will result in an increase in outlet flow angle at the same condition.
[中图分类号]
TK473
[基金项目]
中央高校基本科研业务费专项资金资助项目(3203007403)