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contributor authorWhitfield, Christopher A.
contributor authorSchroeder, Robert P.
contributor authorThole, Karen A.
contributor authorLewis, Scott D.
date accessioned2017-05-09T01:24:43Z
date available2017-05-09T01:24:43Z
date issued2015
identifier issn0889-504X
identifier otherturbo_137_09_091004.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/159964
description abstractFilm cooling and sprayed thermal barrier coatings (TBCs) protect gas turbine components from the hot combustion gas temperatures. As gas turbine designers pursue higher turbine inlet temperatures, film cooling and TBCs are critical in protecting the durability of turbomachinery hardware. One obstacle to the synergy of these technologies is that TBC coatings can block cooling holes when applied to the components, causing a decrease in the film cooling flow area thereby reducing coolant flow for a given pressure ratio (PR). In this study, the effect of TBC blockages was simulated on film cooling holes for widely spaced cylindrical and shaped holes. At low blowing ratios for shaped holes, the blockages were found to have very little effect on adiabatic effectiveness. At high blowing ratios, the areaaveraged effectiveness of shaped and cylindrical holes decreased as much as 75% from blockage. The decrease in areaaveraged effectiveness was found to scale best with the effective momentum flux ratio of the jet exiting the film cooling hole for the shaped holes.
publisherThe American Society of Mechanical Engineers (ASME)
titleBlockage Effects From Simulated Thermal Barrier Coatings for Cylindrical and Shaped Cooling Holes
typeJournal Paper
journal volume137
journal issue9
journal titleJournal of Turbomachinery
identifier doi10.1115/1.4029879
journal fristpage91004
journal lastpage91004
identifier eissn1528-8900
treeJournal of Turbomachinery:;2015:;volume( 137 ):;issue: 009
contenttypeFulltext


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