Combustion chamber of gas turbine

The invention relates to the technical field of aerospace equipment, in particular to a combustion chamber of a gas turbine. The problems that the working range is not wide enough and the selectable type of fuel is narrow are solved. The combustor comprises a cartridge receiver, a rotating cylinder, an ignition electric nozzle and a flame tube, the two ends of the rotating cylinder penetrate through and are coaxially arranged at an opening of the smaller end of the cartridge receiver in a penetrating mode, the ignition electric nozzle is coaxially arranged in the rotating cylinder, one end of the rotating cylinder extends into the cartridge receiver and then is sequentially provided with a first-stage swirler and a second-stage swirler in the circumferential direction, and the second-stage swirler is coaxially and fixedly connected with the flame tube. And a first fuel channel, a second fuel channel, a third fuel channel, a fourth fuel channel and a fifth fuel channel which are sequentially arranged outwards