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TECHNICAL PAPERS

An Experimental Evaluation of Advanced Leading Edge Impingement Cooling Concepts

[+] Author and Article Information
M. E. Taslim, L. Setayeshgar

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

S. D. Spring

GE Aircraft Engines, Lynn, MA 03885

J. Turbomach 123(1), 147-153 (Feb 01, 2000) (7 pages) doi:10.1115/1.1331537 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

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Figures

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Schematic of the test apparatus
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Target surface geometries
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a) Inflow and b) outflow arrangements
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Percentage of air-flow rate through each impingement hole for the two inflow arrangements
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Nusselt number variation with Reynolds number for geometry 1 (smooth wall), flow from one end
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Nusselt number variation with Reynolds number for geometry 1 (smooth wall), flow from both ends
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A comparison between the results of inflow from one end and inflow from both ends for geometry 1 (smooth wall), Z/djet=5.2
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A comparison between the heat transfer results of all four target wall geometries in nominal flow arrangement
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A comparison between the heat transfer results of symmetric and asymmetric impingement on geometry 3 (cones), Z/djet=5.2
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A comparison between the heat transfer results of all four target wall geometries in one-sided outflow arrangement
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A comparison between the heat transfer results of all four target wall geometries in crossflow arrangement
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A comparison between the area-augmented heat transfer results of all four target wall geometries in nominal outflow arrangement
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A comparison between the area-augmented heat transfer results of all four target wall geometries in crossflow arrangement
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A comparison between the area-augmented heat transfer results of all four target wall geometries in one-sided outflow arrangement

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