Abstract: Taking the combustor liner of F-class gas turbine as the research object, analysis was carried out on the internal flow field, temperature field and stress field of the combustor liner under rating operation conditions based on fluid-thermal-solid coupling method, considering the effect of thermal barrier coatings and cooling structures on the aerodynamic heat transfer of the combustor liner. The results of numerical analysis were compared with the actual damage situation of the combustor liner. Results show that the high stress areas are basically consistent with the actual damaged regions of the combustor liner, thus the fluid-thermal-solid coupling method can be used to predict the damage situation of the combustor liner. The ceramic layers of the thermal barrier coatings at different locations have similar insulation effect. Both the substrate and the ceramic layers of the thermal barrier coatings in the vicinity of the cooling structures are areas of high stress.