The invention relates to the technical field of a gas turbine, and particularly discloses a combustion chamber of the gas turbine. The combustion chamber comprises a combustion pressure cylinder, a turbine box, an end cover, a spray nozzle, a flow guiding bush, a flame tube and a transition section, wherein the rear end of the turbine box is connected with the combustion pressure cylinder, the end cover is connected to the front end of the turbine box, the spray nozzle is connected to the end cover, the flow guiding bush is connected to the inner side of the turbine box, the flame tube is positioned in the flow guiding bush, the front end of the flame tube is connected with the spray nozzle, and an inlet of the transition section is connected with the rear end of the flame tube; an output guide vane is arranged in an output of the transition section, the transition section and the output guide vane are of an integrated structure, and air distribution cavities are formed in the output guide vane and the end wall of the front edge of the output guide vane of the transition section. According to the combustion chamber of the gas turbine, disclosed by the invention, the cooling flow of the end wall of the front edge of a primary stationary blade is saved, and the overall efficiency is increased.