涡轮导向叶片综合冷却效率实验研究  

Experimental Investigation on Overall Cooling Effectiveness of Turbine Guide Vane

作　　者：王培枭 郭昊雁[2] 李杰 杨卫华[1] WANG Pei-xiao;GUO Hao-yan;LI Jie;YANG Wei-hua(College of Energy and Power Engineering,Nanjing University of Astronautics and Aeronautics,Nanjing 210016,China;Beijing Power Machinery Research Institute,Beijing 100074,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]北京动力机械研究所,北京100074

出　　处：《推进技术》2019年第7期1568-1576,共9页Journal of Propulsion Technology

基　　金：北京动力机械研究所对本研究的资助和支持

摘　　要：为了研究流动参数对涡轮导向叶片综合冷却效率的影响,采用红外热像仪对叶片表面的温度分布进行了测量,得到了叶片的综合冷却效率随流量比、温比、主流进口雷诺数和湍流度的变化规律。实验过程中,次流与主流的流量比分别为0.15,0.18,0.20,0.22和0.24;主次流温比分别为1.4,1.7,1.93和2.2;主流进口雷诺数分别为1.0×10^5,1.1×10^5,1.2×10^5,1.3×10^5和1.4×10^5;主流进口湍流度分别为0.506%,8.156%,14.92%。结果表明,综合冷却效率在前缘处最低,沿流向逐渐升高;增大流量比会显著提高叶片的综合冷却效率,在温比为1.93时,流量比由0.15增大至0.24,综合冷却效率平均增加29.3%;温比和主流进口湍流度的增大均不利于综合冷却效率的提升,流量比为0.20时,温比由1.4增大至2.2,综合冷却效率平均下降46.5%,湍流度由0.506%增大至14.92%,综合冷却效率平均降低15.5%;主流进口雷诺数对叶片综合冷却效率的影响很小。In order to study the effects of flow parameters on the overall cooling effectiveness of turbine guide vanes,the temperature distribution on the blade surface was measured by infrared thermograph,and the variation of the overall cooling effectiveness with mass flow ratio,temperature ratio,mainstream inlet Reynolds number and turbulence intensity was obtained. During the experiment,the coolant-to-mainstream mass flow ratios were 0.15,0.18,0.20,0.22 and 0.24;the mainstream-to-coolant temperature ratios were 1.4,1.7,1.93 and 2.2,the mainstream inlet Reynolds numbers were 1.0×10^5,1.1×10^5,1.2×10^5,1.3×10^5 and 1.4×10^5,and the mainstream inlet turbulence intensities were 0.506%,8.156% and 14.92%,respectively. The results show that the overall cooling effectiveness is the lowest at the leading edge and increases gradually along the flow direction. Increasing the mass flow ratio can significantly improve the overall cooling effectiveness of the blade. When the temperature ratio is 1.93,the overall cooling efficiency increases by 29.3% on average as the mass flow ratio increases from 0.15 to 0.24. The increase of temperature ratio and mainstream inlet turbulence intensity is not conducive to the improvement of the overall cooling effectiveness. When the mass flow rate is 0.20,the overall cooling efficiency decreases by 46.5% and 15.5% on average with the increase of temperature ratio from 1.4 to 2.2 and the turbulence intensity from 0.506% to 14.92%. The mainstream inlet Reynolds number has little effect on the overall cooling effectiveness of the blade.

关 键 词：综合冷却效率 涡轮导向叶片 流量比 温比 雷诺数 湍流度 

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]