Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number

Figure 25

Normalized Integrated Aerodynamic Loss values for different hole configurations for film injection from both rows of holes, for cambered vanes with film cooling [55]. Symbols are defined in Figure 24. Lines are determined using (17) and 𝐶₁ values from Table 3.