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contributor authorW. Colban
contributor authorK. A. Thole
contributor authorM. Haendler
date accessioned2017-05-09T00:30:46Z
date available2017-05-09T00:30:46Z
date copyrightJuly, 2008
date issued2008
identifier issn0889-504X
identifier otherJOTUEI-28748#031007_1.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/139480
description abstractFan-shaped film-cooling holes have been shown to provide superior cooling performance to cylindrical holes along flat plates and turbine airfoils over a large range of different conditions. Benefits of fan-shaped holes include less required cooling air for the same performance, increased part lifetime, and fewer required holes. The major drawback, however, is increased manufacturing cost and manufacturing difficulty, particularly for the vane platform region. To this point, there have only been extremely limited comparisons between cylindrical and shaped holes on a turbine endwall at either low or high freestream turbulence conditions. This study presents film-cooling effectiveness measurements on an endwall surface in a large-scale, low-speed, two-passage, linear vane cascade. Results showed that film-cooling effectiveness decreased with increasing blowing rate for the cylindrical holes, indicating jet liftoff. However, the fan-shaped passage showed increased film-cooling effectiveness with increasing blowing ratio. Overall, fan-shaped holes increased film-cooling effectiveness by an average of 75% over cylindrical holes for constant cooling flow.
publisherThe American Society of Mechanical Engineers (ASME)
titleA Comparison of Cylindrical and Fan-Shaped Film-Cooling Holes on a Vane Endwall at Low and High Freestream Turbulence Levels
typeJournal Paper
journal volume130
journal issue3
journal titleJournal of Turbomachinery
identifier doi10.1115/1.2720493
journal fristpage31007
identifier eissn1528-8900
keywordsFlow (Dynamics)
keywordsCooling
keywordsTurbulence AND Coolants
treeJournal of Turbomachinery:;2008:;volume( 130 ):;issue: 003
contenttypeFulltext


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