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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

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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