Abstract: This paper provides a calculating model for the temperature field of a multi layer and multi hole wall with complex boundary conditions. The factors, such as convective heat transfer on the inner and outer surfaces, convective heat transfer within the small holes and thermal radiation from combustion gas to the outer surface, are considered. As an example, the temperature field of a full coverage film cooled turbine vane with ceramic coating is calculated. The calculated results show that: (a) ceramic coating has obvious effect of heat insulation and can reduce coolant air flow significantly; (b) the temperature of combustion gas has a large effect on wall temperature; (c) considering thermal radiation will more closely fit the practical physical process; (d) the wall temperature may be underestimated 1. 5%～3. 5% to turbine vane without considering thermal radiation. The model of this paper could be used for optimum design of high temperature components of engines with the cooling construction of multi layer and multi hole walls.

Key words: multi-layer and multi-ho le wall, air craft eng ine, heat transfer, film coo ling, thermal r adiatio n