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TECHNICAL PAPERS

Flow Characteristics in Two-Leg Internal Coolant Passages of Gas Turbine Airfoils With Film-Cooling Hole Ejection

[+] Author and Article Information
D. Chanteloup, A. Bölcs

Ecole Polytechnique Fédérale de Lausanne (EPFL), Laboratoire de Thermique appliquée et de Turbomachines (LTT), 1015 Lausanne, Switzerland

J. Turbomach 124(3), 499-507 (Jul 10, 2002) (9 pages) doi:10.1115/1.1480412 History: Received June 01, 2001; Revised March 06, 2002; Online July 10, 2002
Copyright © 2002 by ASME
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References

Figures

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The internal coolant passage test facility and turn region details
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Measurement sections. The symbols represent the measurement lines (Y direction) that will be analyzed in the next sections (Figs. 5 and 6).
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Hole velocity profile and remaining bulk massflow along the hole configuration centerline
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Mean streamwise velocity contours and secondary flow vectors obtained at θ=0, 45, 90, 135, and 180 deg in the bend. The contour lines values, Uθ, are plotted on the figures (Uθ/Ub).
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Streamwise velocity contours immediately downstream of the bend, 0.0<X<4.0 at three distances from the bottom wall (U/Ub)
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Centerline velocity profiles differences (baseline-hole), normalized by Ub. {a: Streamwise velocity: U; b: radial velocity (from the web toward the outer walls, i.e. 1:along Z-axis: W; 2: along r-axis: Ur; 3:along Z-axis:-W); c: vertical velocity along Y-axis: V;} (e.g., Fig. 2 for exact locations in the rib modules).

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