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TECHNICAL PAPERS

A Three-Dimensional Coupled Internal/External Simulation of a Film-Cooled Turbine Vane

[+] Author and Article Information
James D. Heidmann

NASA Lewis Research Center, Cleveland, OH 44135

David L. Rigby

Dynacs Engineering Co., Inc., Brookpark, OH 44142

Ali A. Ameri

AYT Corporation, NASA Lewis Research Group, Cleveland, OH 44135

J. Turbomach 122(2), 348-359 (Feb 01, 1999) (12 pages) doi:10.1115/1.555450 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Figures

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Vane cross section and film hole row numbers
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Blade-to-blade view of multiblock computational grid
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Leading edge region of computational grid
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Stagnation temperature contours on plane of fixed span
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Stagnation temperature contours on plane normal to streamwise direction through film hole trailing edges: (a) row 3—pressure side (shaped holes); (b) row 12—suction side (round holes)
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Projected velocity vectors for row 12—suction side (round holes); (a) plane A–A in Fig. 2(a); (b) plane B–B in Fig. 2(a)
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Momentum vectors along hole centerline in row 2
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Film hole exit momentum magnitude profiles
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Film hole exit stagnation temperature profiles
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Film hole exit streamwise angle profiles
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Film hole exit spanwise angle profiles
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Overall Stanton number values near vane leading edge
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Film effectiveness values near vane leading edge
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Adiabatic wall Stanton number values near vane leading edge
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Span-averaged film effectiveness
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Span-averaged Stanton numbers
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Span-averaged Stanton number ratios

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