Experimental investigation on cooling performance of binary cooling gas turbine vane

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 three-vane cascade. The experimental results show that the thermal load at trailing edge decreased and the surface temperature uniformity improved. When T_c/T_g=0.65, P_c/P_g=1.3, and M_c/M_g=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.