The cooling effectiveness with the skin cooled micro cooling of a single gas turbine blade is analyzed numerically. The study use Hypermesh to generate a comprehensive 3D mesh of the domain that consists of air around the blade, skin layer of the blade, the cooling channels that wrap around the blade and the core metallic blade inner core. The micro channels were rectangular channel width of 2.54 mm x 0.39mm and heat transfer coefficient varying from (800and 1100 W/m2K) with the channel inlet velocity being constant. The study examined the flow pattern and the local heat transfer effect on the blade temperature. The results show the comparison of the channel HTC of 800 W/m2k and 1100 W/m2K and the effect of coolant inlet temperature on the blade bulk temperature.
|Commitee:||Serdar, Celik, Soondo, Kweon|
|School:||Southern Illinois University at Edwardsville|
|School Location:||United States -- Illinois|
|Source:||MAI 58/04M(E), Masters Abstracts International|
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