涡轮动叶压力面顶部喷冷对气动性能的影响  

Impact on Aerodynamic Performance of Turbine Rotor by Cooling Air Injection on Top of Pressure Side

作　　者：刘勋 张寅豹[2] 梁晨 李凤桐[3] 

机构地区：[1]中船重工第703研究所燃机事业部,黑龙江哈尔滨150078 [2]天津出入境检验检疫局,天津300201 [3]哈尔滨工业大学,黑龙江哈尔滨150001

出　　处：《节能技术》2016年第1期52-54,60,共4页Energy Conservation Technology

摘　　要：本文采用中心差分格式和多区网格技术,对燃气轮机第一级动叶喷射冷气流场进行了全三维N-S方程数值求解。分析了在端壁不同角度冷气喷射条件下,端壁区域的冷却效率、温度场的分布规律,以及不同角度冷气喷射对叶片端壁区域流场的影响。结果表明,在动叶压力面顶部喷射的冷气很好地覆盖了上端壁表面,起到了很好的冷却效果,喷射方向与端壁夹角较大时,端区的能量损失系数较小,冷却效率较高,与端壁夹角较小时,对端壁冷气覆盖效果较好。In this paper, the endwall film - cooling flow field of a gas turbine cascade with cooling air in- jection at top of pressure side has been studied by central difference scheme and multi -block grid tech- nique. The research is based on the three - dimensional N - S equation solver. By means of analysis of the temperature field, the impact of flow field, and the distribution of film - cooling adiabatic effectiveness in the region of endwall with different cool air injection angles, it is found that the cooling air well covered the surface of endwall, which brought great effect on temperature field of endwall region. Aerodynamic energy loss was lower by large injection angle, and adiabatic efficiency is higher.

关 键 词：涡轮 气膜冷却 气动性能 端壁 

分 类 号：TK474.71[动力工程及工程热物理—动力机械及工程]