Abstract: The combustion chamber is one of the core components in a gas turbine，whose performance is an important index for evaluating the performance of the gas turbine. According to the structural characteristics of the combustion chamber，a comprehensive design method for it is given. Firstly，functional zoning was made on the combustion chamber. Then，the temperature of the main combustion zone was selected based on the emissions of CO and NOx ，and the diameter of the outer cylinder was set in light of empirical values.Assuming that the air flow and the air temperature were linearly distributed along the axis，the length of combustion chamber could be chosen based on air residence time .To settle the vents down on the wall of the combustion chamber properly，the general distribution of the three combustion areas should be primarily set from experience and be specified by equivalent area method. Proven by several ignition tests，the combustion chamber designed by the method above has neither flameout nor flame ejection，which shows that the design method is feasible and realizes the rapid and accurate design of the micro gas turbine combustion chamber.

Key words: micro gas turbine, combustion chamber, fuel, residence time, vent on the wall, equivalent area method