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TECHNICAL PAPERS

Toward Improved Rotor-Only Axial Fans—Part I: A Numerically Efficient Aerodynamic Model for Arbitrary Vortex Flow

[+] Author and Article Information
D. N. So̸rensen, J. N. So̸rensen

Department of Energy Engineering, Technical University of Denmark, DK2800 Lyngby, Denmark

J. Fluids Eng 122(2), 318-323 (Jan 21, 2000) (6 pages) doi:10.1115/1.483275 History: Received October 21, 1997; Revised January 21, 2000
Copyright © 2000 by ASME
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References

Cumpsty, N. C., 1989, Compressor Aerodynamics, Longman Scientific & Technical.
Lakshminarayana, B., 1995, Fluid Dynamics and Heat Transfer of Turbomachinery, Wiley, New York.
Üçer, A. S., Stow, P., and Hirsch, C., 1985. “Thermodynamics and Fluid Mechanics of Turbo-Machinery,” Proceedings, Izmir 1984 1-2, Nijhoff.
Novak,  R. A., 1967, “Streamline Curvature Computing Procedures for Fluid-Flow Problems,” ASME J. Eng. Power, 89, pp. 478–490.
Wallis, R. A., 1961, Axial Flow Fans. Design and Practice, George Newnes Limited, London. .
Downie,  R. J., Thompson,  M. C., and Wallis,  R. A., 1993, “An Engineering Approach to Blade Designs for Low to Medium Pressure Rise Rotor-Only Axial Fans,” Exp. Therm. Fluid Sci., 6, pp. 376–401.
Kahane, A., 1948, “Investigation of Axial-Flow Fan and Compressor Rotors Designed for Three-Dimensional Flow,” Tech. Note 1652, NACA, Langley Memorial Aeronautical Laboratory, Langley Field, Va.
Horlock, J. H., 1978, Actuator Disk Theory. Discontinuities in Thermo-Fluid Dynamics, McGraw-Hill, New York.
So̸rensen, D. N., 1998, “Aerodynamic Modelling and Optimization of Axial Fans,” Thesis ET-PHD 9801, Department of Energy Engineering, Technical University of Denmark, DK2800 Lyngby.
Emery, J. C., Herrig, L. J., Erwin, J. R., and Felix, A. R., 1958, “Systematic Two-Dimensional Cascade Tests of NACA 65-series Compressor Blades at Low Speeds,” Report TR-1368, NACA, Langley Aeronautical Laboratory, Langley Field, Va.
Wallis, R. A., 1993, Axial Flow Fans and Ducts, Krieger Publishing, Malabar, FL
Lakshminarayana, B., and Horlock, J. H., 1967, “Leakage and Secondary Flow in Compressor Cascades,” Report R & M 3483, British Aeronautical Research Council.

Figures

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The computational domain with indices for the ith control volume
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Coordinate system showing the rotating blade element and the velocities experienced by the blade element. Cut in the (x-θ) plane (constant r).
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Measured and calculated efficiency at various flow rates. ηtotal and ηstatic are based on the total and static pressure rise across the fan, respectively.
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Measured and calculated pressure rise at various flow rates. pt,total and pt,static denotes the total and static pressure rise, respectively.
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Spanwise distribution of axial velocity far downstream of the rotor at two flow rates
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Spanwise distribution of tangential velocity far downstream of the rotor at two flow rates
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Spanwise distribution of static pressure far downstream of the rotor at two flow rates

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