The high-temperature thermocouple for measuring aero-engine combustor exit temperature were calibrated in the high-temperature wind tunnel

and radiation correction coefficients were experimentally determined for two types of non-cooled and air-cooled thermocouples. Results of the calibration experiment presented that the radiation errors decreased with increasing airflow velocity and pressure

and it became greater when the temperature difference increased between the airflow temperature and aero-engine case wall temperature. Comparing the two types of thermocouple

the measurement errors of the non-cooled high-temperature thermocouple were smaller than the air-cooled high-temperature thermocouple.