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TECHNICAL PAPERS

An Experimental Study of Impingement on Roughened Airfoil Leading-Edge Walls With Film Holes

[+] Author and Article Information
M. E. Taslim, Y. Pan

Mechanical, Industrial, and Manufacturing Engineering, Northeastern University, Boston, MA 02115

S. D. Spring

GE Aircraft Engines, Lynn, MA 02010

J. Turbomach 123(4), 766-773 (Feb 01, 2001) (8 pages) doi:10.1115/1.1401035 History: Received February 01, 2001
Copyright © 2001 by ASME
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References

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Figures

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Schematic of test apparatus
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Inflow and outflow arrangements
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Target surface geometries
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Nusselt number variation with Reynolds number for geometry 1 (smooth wall) and all flow arrangements
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Nusselt number variation with Reynolds number for geometry 2 (bigger cones) and all flow arrangements
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Nusselt number variation with Reynolds number for geometry 3 (smaller cones) and all flow arrangements
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Nusselt number variation with the percentage of showerhead flow for geometry 3 (smaller cones) at different Reynolds numbers
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Nusselt number variation with Reynolds number for geometry 4 (ribs) and all flow arrangements
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Comparison between heat transfer results of all target surface geometries with 100 percent showerhead flow
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Comparison between the area-augmented heat transfer results of all target surface geometries with 100 percent showerhead flow
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Comparison between heat transfer results of all target surface geometries with 50 percent showerhead flow
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Comparison between the area-augmented heat transfer results of all target surface geometries with 50 percent showerhead flow
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Comparison between the heat transfer results of all target surface geometries with 70 percent showerhead and 30 percent crossflow
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Comparison between the area-augmented heat transfer results of all target surface geometries with 70 percent showerhead and 30 percent crossflow
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Pressure ratio across the jet plate versus Reynolds number for geometry 1 (smooth wall) and all flow arrangements
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Pressure ratio across the jet plate versus Reynolds number for all geometries and 100 percent showerhead flow

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