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

<table>Comparison of vane wake total pressure loss coefficient profiles with similar data from Ames and Plesniak [<a href="/journals/ijrm/2012/957421/#B3">3</a>]. The present data are measured 0.25 axial chord lengths downstream of a cambered vane with <svg height="16.0625" id="M195" style="vertical-align:-3.40977pt" version="1.1" viewbox="0 0 76.824997 16.0625" width="76.824997" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
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<g transform="matrix(.017,-0,0,-.017,32.688,11.762)"><use xlink:href="#x3D"></use></g><g transform="matrix(.017,-0,0,-.017,47.374,11.762)"><use xlink:href="#x1D7CE"></use></g><g transform="matrix(.017,-0,0,-.017,55.874,11.762)"><use xlink:href="#x2E"></use></g><g transform="matrix(.017,-0,0,-.017,59.75,11.762)"><path d="M58 524l-21 12q80 152 229 152q73 0 119 -41q45 -41 45 -96q0 -40 -21.5 -74.5t-62.5 -52.5q57 -20 89.5 -68.5t32.5 -109.5q0 -110 -86 -185t-214 -75q-69 0 -110.5 24.5t-41.5 65.5q0 26 18.5 43t46.5 17q45 0 96 -57q39 -43 79 -43q45 0 71.5 34t26.5 88q0 75 -49 121
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</svg> [<a href="/journals/ijrm/2012/957421/#B48">37</a>].</table>

International Journal of Rotating Machinery

fig14

Figure 14

Figure 14: Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 

Figure 14 | Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 