涡轮叶片前腔冲击/气膜复合冷却与单一气膜冷却结构对比实验研究

In order to compare the flow and heat transfer characteristics of the impingement/film and pure film cooling structure for the turbine vane, a comprehensive conjugate heat transfer experiment was carried out for the complete vane with low thermal conductivity material. The film cooling and impingement/film cooling structures were used to the pressure surface of the test vanes leading cavity respectively. In the experiment, the temperature distribution on the surface of the vane was measured with an infrared thermal imager, and the effects of the blowing ratio (M) on the integrated cooling efficiency were analyzed. The effects of two cooling structures on the cooling efficiency of turbine vanes under different experimental conditions were studied. The results show that due to the uneven pressure distribution on the vane surface, the cooling efficiency of the first film hole closer to the leading edge is lower than that of the second row, and the smaller the blowing ratio is, the more obvious this phenomenon will be. Compared with the traditional film cooling vane, the cooling efficiency of the impingement/film cooling vane increased by 3.45%, 6.33%, and 5.64% under the conditions of M=0.4 , 1.2, and 2.0, respectively. At the same time, the kinetic energy loss of the coolant caused by impingement cooling can weaken the phenomenon that the coolant detaches from the vane wall after flowing out at a high blowing ratio.