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

<table>Profiles measured at one axial chord length downstream of the cambered vane for <svg height="16.0625" id="M207" 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">
<g transform="matrix(.017,-0,0,-.017,.062,11.762)"><use xlink:href="#x1D40C"></use></g>
<g transform="matrix(.012,-0,0,-.012,16.112,15.838)"><use xlink:href="#x1D41E"></use></g><g transform="matrix(.012,-0,0,-.012,21.396,15.838)"><use xlink:href="#x1D431"></use></g>
<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="M62 676h415l-235 -676h-95l200 539h-199q-47 0 -68.5 -18t-36.5 -67h-26z" id="x1D7D5"></path></g><g transform="matrix(.017,-0,0,-.017,68.249,11.762)"><use xlink:href="#x1D7CF"></use></g>
</svg> [<a href="/journals/ijrm/2012/957421/#B49">38</a>]. (a) Normalized local total pressure losses. (b) Normalized local Mach numbers. (c) Normalized local kinetic energy. (d) <svg height="11.425" id="M208" style="vertical-align:-0.0pt" version="1.1" viewbox="0 0 12.9875 11.425" width="12.9875" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
<g transform="matrix(.017,-0,0,-.017,.062,11.363)"><path d="M719 146l-18 -146h-243l-5 18q2 4 17 25t24 36l25 42t26.5 52.5t21 56.5t16 65t5.5 68q0 121 -55.5 194.5t-149.5 73.5q-95 0 -150 -72t-55 -199q0 -54 18.5 -114t36.5 -94t48.5 -82.5t32.5 -51.5l-7 -18h-244l-17 146l27 1q17 -49 31.5 -62t45.5 -13h89l-21 21t-26 26.5
l-26 29t-28 35.5l-23 37.5t-20.5 43t-12 45.5t-5.5 51q0 133 88 218.5t219 85.5q132 0 218 -83t86 -218q0 -40 -11.5 -78t-33 -71.5t-39 -56t-44 -51t-32.5 -35.5h84q35 0 48 12t31 63z" id="x3A9"></path></g>
</svg> total pressure loss coefficient.</table>

International Journal of Rotating Machinery

fig15

Figure 15

Figure 15: Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 

Figure 15 | Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 