Sampler and gas analysis system were introduced for temperature field of aeroengine combustor

and error was analyzed as a result of gas system simplification. Method of computing combustion temperature was expounded

the average of combustion efficiency and combustion temperature and fuel-air ratio was computed. The temperature field for combustor with five nozzles by gas analysis and thermocouple was analyzed

indicating that combustion efficiency by thermocouple was 4% less than that by gas analysis

and combustion temperature was 55℃ lower at 1500℃. Gas analysis was proven to be dominant in measuring high temperature gas from aeroengine combustor. High quality data can be gained by gas analysis

which is hardly influenced by environment.