Abstarct: One way to increase the efficiency of gas turbines is to raise the inlet flow temperature to them. Increasing temperature due to the temperature limit of the alloy material of the turbine blades will endanger its operational life, which with Cooling different areas of the blade will eliminate excessive heat load. Cooling of jet impingement with the highest potential increases the local heat transfer coefficient, reduces the effects of Stagnation Point, and also reduces the heat transfer rate at the leading edge as the most critical area of the blade against the collision of hot fluid flow. In this study, three-dimensional numerical simulation of four concave channels with arrangement, number and shape of multiple tangential and vertical jets in combination and individually with the aim of comparing the amount and distribution of total channel pressure drop and heat transfer on the target surface in Reynolds range 10000 and 150000 in stationary. In all cooling channels, the total area of all spray jet holes is equal to the target surface. To validate the numerical results, several turbulence models have been used, which has provided the best numerical result according to the laboratory results of the Spalart Almaras turbulence model. It has been observed in the study that the flow rate from the jet holes is increasing from the upstream to the downstream in all the studied cases. Considering the constant temperature for the target surface, the Nusselt rate of vertical cylindrical jets was the highest and in comparison with tangential jets as well as the combination of vertical tangential jets with different diameters were about 57% and 16%, respectively. Also, the tangential-vertical hybrid jet with the same diameters had the lowest Nusselt distribution in the concave plane. The amount of pressure drop and friction in the studied channels were not significantly different from each other.