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TECHNICAL PAPERS

Effects of Periodic Inflow Unsteadiness on the Time-Averaged Velocity Field and Pressure Recovery of a Diffusing Bend With Strong Curvature

[+] Author and Article Information
M. I. Yaras, P. Orsi

Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, Canada K1S 5B6

J. Fluids Eng 126(2), 229-237 (May 03, 2004) (9 pages) doi:10.1115/1.1667887 History: Received October 30, 2002; Revised October 02, 2003; Online May 03, 2004
Copyright © 2004 by ASME
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References

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Dolan, F. X. and Runstadler, P. W., 1973, “Pressure Recovery Performance of Conical Diffusers at High Subsonic Mach Numbers,” NASA Contractor Report 2299.
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Yaras,  M. I., 1996, “Effects of Inlet Conditions on the Flow in a Fishtail Curved Diffuser With Strong Curvature,” J. Fluids Eng., 118, pp. 772–778.
Yaras,  M. I., 1999, “Flow Measurements in a Fishtail Diffuser with Strong Curvature,” J. Fluids Eng., 121, pp. 410–417.
Dobbeling,  K., Lenze,  B., and Leuckel,  W., 1990, “Computer-aided Calibration and Measurements with a Quadruple Hotwire Probe,” Exp. Fluids, 8, pp. 257–262.
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Saroch, M. F., 1996, “Contributions to the Study of Turbomachinery Aerodynamics, Part I: Design of a Fish-Tail Diffuser Test Section, Part II: Computations of the Effects of AVDR on Transonic Turbine Cascades,” Masters thesis, Department of Mechanical and Aerospace Engineering, Carleton University.
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Figures

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Fishtail-shaped diffuser test section
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Geometry of the diffuser flow path
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Unsteady-flow generator
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Ensemble-averaged velocity distribution in Plane A (0 to 89% of period) (uncertainties: ±2% for the velocity magnitude and ±1.5 deg for the flow direction)
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Time-averaged velocity distributions along the a) y axis (z=0),b) z axis (y=0) in Plane A. (Uncertainty in V/VCLA=±2%.)
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Time-averaged velocity distribution. (Uncertainties: ±2% for the velocity magnitude and ±1.5 deg for the flow direction.)
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Time-averaged streamwise vorticity distribution. (Uncertainty in streamwise vorticity=±0.05.)
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Time-averaged axial velocity distribution along the y axis (z=0) in Plane B. (Uncertainty in V/VCLA=±2%.)
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Streamwise variations of flow distortion. (Uncertainty in α and αp=±0.05.)

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