Review Article

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

Figure 24

Normalized Integrated Aerodynamic Loss values for different hole configurations for film injection from the first row of holes only, for cambered vanes with film cooling [55]. Lines are determined using (17) and values from Table 3.
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