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TECHNICAL PAPERS

Controlling Secondary-Flow Structure by Leading-Edge Airfoil Fillet and Inlet Swirl to Reduce Aerodynamic Loss and Surface Heat Transfer

[+] Author and Article Information
T. I-P. Shih, Y.-L. Lin

Department of Mechanical Engineering, Michigan State University, East Lansing, MI 48824-1226

J. Turbomach 125(1), 48-56 (Jan 23, 2003) (9 pages) doi:10.1115/1.1518503 History: Received January 03, 2002; Online January 23, 2003
Copyright © 2003 by ASME
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References

Figures

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Basic leading-edge fillet geometries—(a) sharp/pointed, (b) rounded, (c) bulb type
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Schematic of the nozzle vane studied (not drawn to scale)
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Three-dimensional rendering of the nozzle vane studied
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Fillet configurations studied—C1: no fillet, C2: merge on airfoil, C3: merge on endwall
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Illustration of swirls investigated—(a) no swirl with 1/7th profile; (b) S1 swirl (2-D view); (c) S1 swirl (3-D view). S2 is just the opposite of S1 and so is not shown.
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Multiblock grid system used (not all grid lines shown)
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Grid system about the airfoil/flat-endwall junction (not all grid lines shown)—(a) C1, (b) C2, (c) C3
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Cross-flow velocity vector and magnitude in plane A-A
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Streamlines approaching the airfoil/flat-endwall junction, showing the generation of horseshoe vortices
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Surface pressure and velocity vector near surface (y+ between 10 and 20) at airfoil/flat-endwall junction
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Streamlines near the endwalls and the midplane with S1 swirl (no fillets)—(a) contoured endwall, (b) midplane, (c) flat endwall
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Heat transfer coefficient: no fillet with and without swirl
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Heat transfer coefficient: C2 fillet with and without swirl
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Heat transfer coefficient: C3 fillet with and without swirl

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