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强化传热期刊
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ISSN 打印: 1065-5131
ISSN 在线: 1026-5511

强化传热期刊

DOI: 10.1615/JEnhHeatTransf.2013007086
pages 251-265

NUMERICAL INVESTIGATION ON FILM-COOLING CHARACTERISTICS FROM A ROWOF HOLES WITH RIDGE-SHAPED TABS

Yong Shan
Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Jing-Zhou Zhang
College of Energy and Power Engineering, Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, China; Collaborative Innovation Center of Advanced Aero-Engine, Beij ing, 100191, China

ABSTRACT

A three-dimensional numerical simulation was conducted to investigate the enhanced cooling performances caused by ridge-shaped tabs located at the upstream edge of film-cooling holes. Three covering ratios of ridge-shaped tabs on the film holes and four blowing ratios were considered in the present study. By comparison with cylindrical holes (a baseline case), the presence of ridge-shaped tabs in the nearby region of the primary film-cooling holes mitigates the primary vortices due to the mainstream/coolant-jet interaction and transfers the coolant-jet momentum flux mainly in the streamwise direction. The coolant-jet penetration along the vertical direction is suppressed and the peak velocity along the streamwise direction is augmented under the action of the ridge-shaped tabs, providing an increment in the film-cooling effectiveness and enhancement of the heat transfer coefficient over the baseline case. The ridge-shaped tabs provide enhancements in the cooling effectiveness but at the expense of a large pressure drop. From the present study, it is suggested that a ridge-shaped tab with a middle covering ratio is the best choice.


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