In order to overcome the disadvantages of uneven pressure, uneven swirling flow and uneven cooling effect caused by the linear arrangement of cooling holes in the existing gas turbine blade nozzle from tip to hub, the cooling holes are designed to adapt to the rotation direction of the burner cyclone. In the right-hand direction, from the upstream of the airflow, the cooling hole at the leading edge tip of the blade is more left than that at the hub. In the case of left rotation, from the upstream of the flow, the cooling hole at the leading edge tip of the blade is closer to the right than the cooling hole at the hub. In this way, the pressure, flow field and cooling effect can be uniform at each cooling hole.