The invention belongs to the technical field of aero-engine design, and relates to a combustion chamber combustor of a gas turbine. A fuel delivery pipeline of the combustion chamber combustor comprises an auxiliary-stage fuel gas pipe at the innermost layer, an auxiliary-stage sleeve, an inner pipe and an outer pipe, wherein the auxiliary-stage sleeve, the inner pipe and the outer pipe are sequentially connected in the radial direction in a sleeve mode, a primary mixing channel is formed between the inner pipe and the outer pipe, and a main-stage swirler is arranged in the main mixing channel; the auxiliary-stage sleeve is connected to the inner wall of the inner pipe through a venturi pipe in a connecting mode, a secondary mixing channel is formed between the auxiliary-stage sleeve and the auxiliary-stage fuel gas pipe, an auxiliary-stage swirler is arranged in the secondary mixing channel, and an auxiliary-stage fuel injection rod extends towards the secondary mixing channel by theauxiliary-stage fuel gas pipe; and a duty-stage fuel gas pipe is arranged in the auxiliary-stage fuel gas pipe in a sleeve mode, and fuel is sprayed in a combustion chamber flame pipe through a duty-stage fuel spraying nozzle. According to the combustion chamber combustor, the two stages axial swirlers, the three stages fuel nozzles and a venturi structure are arranged to realize premixed combustion of the fuel, the grading effect of the head part of the combustion chamber is optimized, the ignition performance of the combustor is improved while low NOx emission is realized, and the complexityof a fuel system is reduced.