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

<table>Comparison of dimensional integrated aerodynamic loss as dependent upon the normalized equivalent sandgrain roughness size for <svg height="12.0625" id="M252" style="vertical-align:-0.1911pt" version="1.1" viewbox="0 0 93.949997 12.0625" width="93.949997" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
<g transform="matrix(.017,-0,0,-.017,.062,11.762)"><use xlink:href="#x1D413"></use></g><g transform="matrix(.017,-0,0,-.017,11.401,11.762)"><use xlink:href="#x1D42E"></use></g><g transform="matrix(.017,-0,0,-.017,25.561,11.762)"><use xlink:href="#x3D"></use></g><g transform="matrix(.017,-0,0,-.017,40.265,11.762)"><use xlink:href="#x1D7CF"></use></g><g transform="matrix(.017,-0,0,-.017,48.764,11.762)"><use xlink:href="#x2E"></use></g><g transform="matrix(.017,-0,0,-.017,52.64,11.762)"><use xlink:href="#x1D7CF"></use></g><g transform="matrix(.017,-0,0,-.017,62.091,11.762)"><path d="M535 230h-483v50h483v-50z" id="x2212"></path></g><g transform="matrix(.017,-0,0,-.017,73.004,11.762)"><use xlink:href="#x1D7CF"></use></g><g transform="matrix(.017,-0,0,-.017,81.504,11.762)"><use xlink:href="#x2E"></use></g><g transform="matrix(.017,-0,0,-.017,85.379,11.762)"><use xlink:href="#x1D7D4"></use></g>
</svg> percent for a cambered vane [<a href="/journals/ijrm/2012/957421/#B49">38</a>].</table>

International Journal of Rotating Machinery

fig17

Figure 17

Figure 17: Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 

Figure 17 | Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 