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TECHNICAL PAPERS

Predictions of External Heat Transfer for Turbine Vanes and Blades With Secondary Flowfields

[+] Author and Article Information
K. Hermanson, S. Kern, G. Picker, S. Parneix

Alstom Power (Switzerland), CH-5401 Baden, Switzerland

J. Turbomach 125(1), 107-113 (Jan 23, 2003) (7 pages) doi:10.1115/1.1529201 History: Received November 05, 2001; Online January 23, 2003
Copyright © 2003 by ASME
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References

Figures

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Computational domain for rotor blade benchmarking
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Stator vane geometry with analysis planes
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(a) Pitchwise averaged Stanton number presented as % difference from baseline grid (2.1×106 cells); (b) normalized velocity magnitude in plane SP on a spanwise line at X/C=−0.088
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Leading edge horseshoe vortex roll-up in plane SP—(a) measurements 4, (b) realizable k-ε with wall functions, (c) realizable k-ε two-layer model, (d) V2F model
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Pitch angles, ϕ, on plane PS-2—(a) realizable k-ε two-layer model, (b) V2F model, (c) measurements 24
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Pitchwise-averaged Stanton numbers
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Contours of Stanton number on the endwall—(a) RKE 2-layer, (b) V2F, (c) experimental measurements 5
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Heat transfer at midspan
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Contours of heat transfer on the suction surface of the vane
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Secondary flow in blade geometry
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Contours of Stanton number on the endwall for the rotor blade geometry—(a) experiment 7, (b) V2F model
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Heat transfer along the span of the suction side of the airfoil

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