A micro gas turbine combustor using natural gas as fuel was designed

and its combustion characteristics were tested. The combustor is baffled type single-tube combustion chamber with single stage swirler + primary combustion hole. The gas flow in the combustor can realize a 180° turn by applying an L-type gas conduit. The fuel nozzle is a porous type

and the injection angle of the two rows of holes is 120° and 90°. The requirements of temperature field at outlet of the combustion chamber can be satisfied by the mutual cooperation between the mixing holes and gas conduit cooling holes. The test results show that

the pressure recovery coefficient was 0.955 and 0.940 for cool and heat condition

respectively. Better ignition characteristics can be obtained when the ignition fuel/air ratio was 0.005～0.007. The main factor affecting the lean burnout characteristics was the combustor entrance temperature

the lean blowout fuel/air ratio decreased from 0.002 6 to0.002 3 when the atmospheric temperature increased from-30 ℃ to 30 ℃. The emission and combustion efficiency failed to meet the requirements

especially the CO emission volume concentration reached 300×10~(–6)

which was high. The pattern factor of the temperature distribution at the outlet of the combustion chamber was below 0.15

which met the requirements

but the unreasonable air flow distribution caused local high temperature on the flame tube.