The invention relates to a turbine rotor blade of a gas turbine. The turbine rotor blade of the gas turbine comprises a blade profile, a blade platform, a blade top and a blade root, wherein a coolingair channel loop is arranged in the blade, a cooling air channel and a cooling air channel inlet are arranged in the loop, and ribs are arranged in the cooling air channel; and the blade surface is divided into a blade leading edge and a blade trail edge by a pressure surface and a suction surface. The blade tail edge is provided with a tail edge exhaust slot, a tail edge channel is provided witha guide groove structure, and at least one turbulence column is arranged in the guide groove structure; and the blade root cooling air channel is divided into at least two channels by a partition plate, and the partition plate is gradually bent towards the front edge side of the blade in the airflow direction. According to the turbine rotor blade of the gas turbine, the heat exchange effect of aleading edge channel, the tail edge exhaust slot and cooling air in the blade can be improved, and the leading edge metal temperature close to the blade platform and the metal temperature of the tailedge, the blade platform close to the tail edge and the blade root can be reduced.