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Improving film cooling performance by using one -inlet and double-outlet hole
Authors:Guang-chao Li  Wei Zhang
Affiliation:Aeroengine and Energy Engineering College, Shenyang Areospace University Shenyang China 110136
Abstract:The film cooling performance of a trunk-branch hole is investigated by numerical simulation in this paper.The geometry of the hole is a novel cooling concept,which controls the vortices-pair existing at the trunk hole outlet using the injection of the branch hole.The trunk-branch holes require easily machinable round hole as compared to the shaped holes.The flow cases were considered at the blowing ratios of 0.5,0.75,1.0,1.5 and 2.0.At the low blowing ratio of 0.5,the vortices-pair at the outlet of the trun...
Keywords:aerospace propulsion system  gas turbine  film cooling  heat transfer  
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