The invention discloses a turbine rotor blade of a gas turbine. The blade comprises a blade profile, a blade root and a blade platform connecting the blade profile with the blade root. The outer surface of the blade profile is composed of a force suction surface and a pressure surface, the junction area of the force suction surface and the pressure surface comprises a blade front edge and a bladetail edge, and a cooling channel structure is arranged in the blade, and comprises cooling channels of at least three cooling blade tail edges. In the area close to the blade tail edge, the tail edgeis at least divided into three areas in the blade height direction, cooling air flows of inlets of the cooling channels of at least three cooling tail edges can be independently adjusted, the expectedcooling distribution effect is easily achieved, and particularly for the blade root area and the blade tip area of the tail edge, the cooling design difficulty of the area can be greatly reduced