Effect of slotted jet on cooling characteristics of turbine guide vane end wall

In order to obtain a higher thrust-to-weight ratio, the combustion temperature of aero-engine is getting higher and higher, which makes the lower edge plate of guide vane subjected to more heat load and prone to ablation. Therefore, it is particularly important to cool the lower edge plate. In this paper, the influence of the leading edge cooling structure on the cooling characteristics of the lower edge plate of the guide blade is studied by numerical calculation. The following conclusions are drawn: (1) When the radial clearance of the front cooling structure is reduced, the momentum increases due to the decrease in the outflow area of cold air, the resistance to transverse secondary flow of the cascade is enhanced, and the cooling effect of the end wall is greatly improved; (2) Reducing the axial clearance of the leading edge cooling structure can reduce the mixing loss of the main stream and cold air, and improve the cooling effect of the end wall.