摘要：Micro-scale cooling structures can significantly improve the heat resistance of turbine blades so that they can still operate effectively in high-temperature environments. In order to achieve the optimal cooling effect of gas turbine blades with the minimum cooling air quantity, experimental and numerical simulations of jet impingement channel flow in a micro-scale composite cooling structure were carried out innovatively in this study. The diameters of shock hole and film hole were taken as 0.3-0.5mm, and the impact distance was between 2.0-3.0. The value of Reynolds number was 1000-10000, and Knudsen number was according to the real engine working conditions. The flow situations of different structure micro-scale shock channels were compared and analyzed. The results show that the flow coefficient increased with the increase of Reynolds number, but its growth trend slowed down with the increase of Reynolds number, and finally tended towards to a constant. For the same value of Reynolds number, the flow coefficient increased with the increase of pore diameter and the hole spacing, but the impact distance had no obvious effect on the flow coefficient. Moreover, the flow coefficient was fitted out and the results of the calculation were in good agreement with the experimental results, which could be used in an actual engineering environment.
