numerical investigation of the effect of thermal barrier coating on heat transfer andwall temperature in v94.2 gas turbine combustor

Thermal barrier coating (tbc) has been considered in current investigation in order to increase mixing chamber and inner casing lifetime in v94.2 gas turbine combustor. these parts are exposed to hot flow produced by burner. based on the mentioned concerns, on the hot side, tbc has been considered. the temperature gradient for turbulent flow and casings are presented. the results have shown that by using tbc, heat flux rate declined notably compared to the case where tbc was not applied. in the existence of tbc, the temperature distribution has changed significantly, which is important in changing the wall temperature of the combustor. the maximum temperature in the mixing chamber decreased by 160 k whereas in the inner casing maximum temperature dropped by 24 k. hot spots in mixing chamber and inner casing are considerably reduced. the heat flux rate in mixing chamber is higher than that of inner casing since the temperature difference and convection heat transfer coefficient in mixing chamber is higher.