For a serpentine internal cooling flow path in which the impingement cavities were located on the pressure side and suction side alternately

the commercial code FLUENT was used for three-dimensional conjugate heat transfer simulation to determine temperature distribution on an air-cooled and thermal barrier coating (TBC) blade.The effect of TBC thickness on the temperature decreasing capacity for blade metal surface was analyzed

and the temperature difference with/without considering radiation heat transfer was also analyzed.In the case of primary flow temperature 1600K and cooling flow temperature 700K

the maximum temperature for the present air-cooled blade can be controlled within 1100K when the cooling massflow is about 7.47% of the primary massflow and the TBC thickness was 0.2mm.The temperature decreasing capacity for TBC reaches about 130-180K when the TBC thickness is 0.15-0.35mm assuming the emissivity of TBC is the same as that of blade metal surface.The temperature difference with/without considering radiation heat transfer is about 60K.