Fan-Shaped Hole Film Cooling on Turbine Blade and Vane in a Transonic Cascade with High Freestream Turbulence: Experimental and CFD Studies
The contribution of present research work is to experimentally investigate the effects of blowing ratio and mainstream Mach number/Reynolds number (from 0.6/8.5X10⁵ to 1.0/1.4X10⁶) on the performance of the fan-shaped hole injected turbine blade and vane. The study was operated with high freestream...
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| Format: | Others |
| Language: | en_US |
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Virginia Tech
2017
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| Online Access: | http://hdl.handle.net/10919/77979 http://scholar.lib.vt.edu/theses/available/etd-07242012-113420/ |