动静干涉对叶栅前缘气膜冷却特性的影响  

Effect of rotor-stator interference on film cooling at leading edge of cascade

作　　者：孙小恺 王振宇 王春华[1,2] SUN Xiaokai;WANG Zhenyu;WANG Chunhua(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing,Jiangsu 210016,China;Jiangsu Province Key Laboratory of Aerospace Power System,Nanjing University of Aeronautics and Astronautics,Nanjing,Jiangsu 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]南京航空航天大学,江苏省航空动力系统重点实验室,江苏南京210016

出　　处：《江苏大学学报（自然科学版）》2021年第6期671-677,共7页Journal of Jiangsu University：Natural Science Edition

摘　　要：针对动静干涉影响下涡轮动叶前缘气膜孔射流与主流的相互作用展开研究,比较分析了叶根、中截面及叶尖区域气膜冷却流场和温度场分布特征的差异.结果表明:随着叶高的增加,前缘滞止线从吸力面侧逐渐向压力面侧偏移,压力面侧气膜射流贴壁性变弱;动静干涉使得气膜射流出现“分流”、“上扬”和“逆流”现象,对中心截面气膜覆盖的影响大于叶根和叶尖区域;气膜射流下游反转涡对呈现明显不对称性,吸力面侧反转涡对强度和尺度沿叶高方向不断降低,而压力面侧反转涡对的变化趋势相反;动静干涉降低了气膜冷却效率.To investigate the interaction between jet flow and main flow at the leading edge of turbine blade under the influence of rotor-stator interference,the differences of flow distribution and temperature distribution at the end wall,the middle section and the tip of turbine blade were compared and analyzed.The results show that with the increasing of blade height,the leading edge stagnation line is gradually shifted from the suction side to the pressure side,and the wall adherence of jet flow on the pressure side is weakened.The phenomena of"divergence","uptrend"and"countercurrent"of jet flow are caused by rotor-stator interference,and the influence on gas film coverage at central section is greater than those at root and tip.In the downstream of jet flow,the inversion of vortex pairs shows obviously asymmetric,and the strength and scale of the vortex pairs on the suction side are decreased along the direction of blade height,while the variation trend of the inversion of vortex pairs on the pressure side is opposite.The rotor-stator interference can reduce the film cooling efficiency.

关 键 词：涡轮 动静干涉 气膜冷却 滞止线 反转涡 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]