The invention relates to a gas turbine combustion chamber arrangement having at least one centrifugal compressor 1 and having a centripetal annular combustion chamber, wherein between the centrifugal compressor 1 and the annular combustion chamber there is arranged a guide blade arrangement 2, characterized in that the guide blade arrangement 2 is designed such that the air flowing out of the centrifugal compressor 1 is diverted at an angle alpha of 20° to 30°, preferably 25°, with respect to the power unit axis 9, in that the air flow is supplied to the combustion chamber at substantially said angle alpha, in that the inflow region into the combustion chamber is designed for supplying the air at an angle of 20° to 30°, preferably 25°, with respect to the meridian plane 12, and in that the central axes 10 of the burners 4 or of the injection nozzles of the combustion chamber are arranged so as to be inclined at an angle beta of 30° to 40°, preferably 35°, with respect to a meridian plane 12 running through the power unit axis 9.