Abstract: The axial staged combustion chamber of the self-developed F-class gas turbine was studied under full temperature and full pressure condition. In order to explore the combustion performance of the combustion chamber under the working conditions of the design point, such as pressure loss, outlet temperature distribution, wall temperature, pollutant discharge, combustion efficiency and thermoacoustic stability, etc. Results show that, the total pressure loss coefficient of the combustion chamber is 5.4% at the design point. The outlet temperature distribution factor and radial temperature distribution factor are 0.06 and 0.03, respectively. And the wall temperature of the flame barrel in the combustion chamber is below 850 ℃. The mole fraction of NO_x is maintained 1.9×10^-5, while the emissions of CO and unburned hydrocarbon（UHC） are basically zero. The combustion efficiency is maintained above 99.99%. The amplitude of dynamic pressure spectrum is below 3 kPa, which indicates the thermoacoustic state of the combustor is stable.