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TECHNICAL PAPERS

Influence of Surface Roughness on Three-Dimensional Separation in Axial Compressors

[+] Author and Article Information
Semiu A. Gbadebo, Tom P. Hynes

Whittle Laboratory, University of Cambridge, Cambridge, United Kingdom

Nicholas A. Cumpsty

Rolls-Royce Plc, Derby, United Kingdom

J. Turbomach 126(4), 455-463 (Dec 29, 2004) (9 pages) doi:10.1115/1.1791281 History: Received October 01, 2003; Revised March 01, 2004; Online December 29, 2004
Copyright © 2004 by ASME
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References

Gbadebo, S. A., Cumpsty, N. A., and Hynes, T. P., 2004, Three-dimensional Separations in Axial Compressors, ASME Paper GT-2004-53617.
Suder, K. L., Chima, R. V., Strazisar, A. J., and Roberts, W. B., 1994, Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor, ASME Paper 94-GT-339.
Bammert,  K., and Woelk,  G. U., 1980, “Influence of the Blading Surface Roughness on the Aerodynamic Behavior and Characteristic of an Axial Compressor,” ASME J. Eng. Gas Turbines Power, 102, pp. 579–583.
Boyle,  R. J., 1994, “Prediction of Surface Roughness and Incidence Effects on Turbine Performance,” ASME J. Turbomach., 116, pp. 745–751.
Cebeci,  T., and Chang,  K. C., 1978, “Calculation of Incompressible Rough-Wall Boundary-Layer Flows,” AIAA J., 16, pp. 730–735.
Chang, P. K., 1970, Separation of Flow, Interdisciplinary and Advanced Topics in Science and Engineering, Vol. 3, Pergamon Press.
Place, J. M. M., 1997, “Three-Dimensional Flow in Axial Compressors,” Ph.D. thesis, University of Cambridge, United Kingdom.
Bolger, J. J., 1999, “Three-Dimensional Design of Compressor Blades,” Ph.D. thesis, University of Cambridge, United Kingdom.
Koch,  C. C., and Smith,  L. H., 1976, “Loss Sources and Magnitudes in Axial Flow Compressors,” ASME J. Eng. Gas Turbines Power, 98, pp. 411–424.
Schlichting, H., 1979, Boundary Layer Theory, McGraw–Hill, New York.
White, F. M., 1991, Viscous Fluid Flow, McGraw–Hill, New York.
Denton,  J. D., 1992, “Calculation of Three-Dimensional Viscous Flows Through Multistage Turbomachines,” ASME J. Turbomach., 114, pp. 18–26.
Denton, J. D., 1999, “Multistage Turbomachinery Flow Calculation Program-MULTIP,” Whittle Laboratory, University of Cambridge, United Kingdom.
Gbadebo, S. A., 2003, “Three-Dimensional Separations in Compressors,” Ph.D. thesis, University of Cambridge, United Kingdom.
Cumpsty, N. A., 1989, Compressor Aerodynamics, Longman Scientific and Technical.

Figures

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Schematic diagram of stator blade with roughness (a) full strip (leading edge to peak-suction); (b) full strip (mid-chord); (c) 50% span from hub (leading edge to peak-suction); (d) full strip (near trailing edge)
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Contours of total pressure rise coefficient at the exit of a smooth and single stator roughened around leading edge/peak-suction at design point, ϕ=0.51 (contour interval=0.03)
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Influence of location of roughness strip on stator exit flow angles at design point, ϕ=0.51
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Suction surface flow visualization on smooth and roughened stator around leading edge/peak-suction at design point, ϕ=0.51
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Contours of stage total pressure rise coefficients for smooth and roughened blade-rows at different flow coefficients. (Roughness from LE to peak-suction.)
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Contours of stage exit total pressure rise coefficient for stepped blade-row at design point, ϕ=0.51. (Roughness from LE to peak-suction.)
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Radial profiles of pitchwise mass-averaged stage total pressure rise coefficients for smooth, stepped and roughened blade-rows and single roughened blade at design point, ϕ=0.51. (Roughness from LE to peak-suction.)
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Radial profiles of pitchwise area-averaged axial velocities for smooth, stepped and roughened blade-rows together with single roughened blade at design point, ϕ=0.51. (Roughness from LE to peak-suction.)
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Radial profiles of pitchwise mass-averaged exit flow angles for smooth, stepped and roughened blade-rows and single roughened blade at design point, ϕ=0.51. (Roughness from LE to peak-suction.)
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Comparison of surface static pressure distribution at different spanwise locations of smooth and roughened blade-rows at design point, ϕ=0.51. (Roughness from LE to peak-suction.)
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Comparison of total-to-total and total-to-static stage pressure rise characteristics for smooth and roughened blade-rows. (Roughness from LE to peak-suction.)
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Numerical suction surface streamlines for smooth and roughened stator at design point, ϕ=0.51
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Predicted contours of exit total pressure rise coefficients for smooth and roughened stator blade at design point, ϕ=0.51. (Roughness from LE to peak suction.)
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Comparison of measured and calculated mass-averaged stage exit total pressure rise coefficients at different operating points for smooth and roughened stator blade. (Roughness from LE to peak suction.)

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