The invention provides a cooling structure of a high-pressure moving blade of a turbine of a gas turbine, and belongs to the technical field of gas turbines. The cooling structure is characterized in that seven channels including a first channel, a second channel, a third channel, a fourth channel, a fifth channel and a sixth channel are sequentially formed in the blade from the front edge of the blade to the tail edge of the blade; the first channel, the second channel, the third channel, the fourth channel, the fifth channel and the sixth channel are provided with turbulent flow ribs, the third channel, the second channel and the first channel are sequentially connected with one another to form a snakelike channel, U-shaped spaces are formed at joints of the adjacent channels, the fourth channel, the fifth channel and the sixth channel are sequentially connected with one another to form a snakelike channel, and U-shaped spaces are formed at joints of the adjacent channels; a first gas inlet, a second gas inlet and a third gas inlet are formed in the bottoms of the third channel, the fourth channel and the seventh channel; a plurality of split seams are formed in the tail edge of the blade, and gas can be exhausted via the split seams; a blade top groove is formed in a blade top, and cooling holes and process holes are formed in the blade top groove; and blade top pressure surface cooling holes are formed in a blade top pressure surface. The cooling structure has the advantages that the front edge of the blade, a suction surface of the blade, the blade top and the like can be sufficiently cooled, accordingly, uniform blade root temperature fields can be guaranteed, the temperature of a blade body can be reasonably distributed, and the cooling structure is low in cold gas flow.