透平叶片双工质冷却特性的实验研究

Experimental Investigation on Cooling Performance of Binary Cooling Gas Turbine Vane

针对双工质冷却叶片存在尾缘温度较高的问题,提出了一种带尾缘射流孔的双工质冷却叶片。在建立的3叶片叶栅热风洞实验平台上,实验研究了冷却介质进口参数对实验叶片表面温度和冷却效率分布的影响。结果表明:双工质综合冷却下,叶片尾缘温度大幅度下降,叶片表面温度分布较均匀;当冷却介质与主流燃气的温比Tc/Tg=0.65、压比Pc/Pg=1.3、流量比Mc/Mg=0.034时,叶片尾缘和前缘区域冷却效率分别约为50%和55%,中弦区域的冷却效率高达67%;与冷却介质进口参数相比,冷却方式和冷却结构对提高叶片冷却效率更有效。

A new binary cooling vane with trailing edge ejection of cooling air was proposed to solve the problem of very high thermal load at the trailing edge of a binary cooling turbine vane.The influence of the coolant inlet parameters on the temperature and cooling effectiveness distribution on the experimental vane surface was investigated in the hot wind tunnel with a threevane cascade.The experimental results show that the thermal load at trailing edge decreased and the surface temperature uniformity improved.When Tc/Tg =0.65,Pc/Pg =1.3,and Mc/Mg =0.034,the cooling effectiveness of the trailing edge region and leading edge region was 50％ and 55％,respectively.The cooling effectiveness of the middle chord region was the highest and reached 67％.In addition,the cooling method and structure had more influence on the cooling effectiveness than the inlet conditions of the cooling fluids.