In order for the enhanced specific fuel consumption and efficiency of aero and industrial gas turbine system, hot components in its system such as turbine vane, turbine blade, and combustor liner, suffer extremely high operating temperature which exceeds allowable material limit. Therefore, sophisticated and elaborate cooling schemes should be implemented in hot components of gas turbine system. 

For thermally durable and reliable thermal-fluid design for turbine blades, we should understand formation of heat flux over turbine blade according to the nature of flow in turbine passage from hot combustion gas. Also, to reduce inflow of heat flux from hot combustion gas, we should investigate thermal-fluid designs for decreasing heat transfer coefficients on turbine external surface and thermal-fluid designs for increasing heat transfer coefficients on turbine internal surface (internal cooling passage surface).