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TECHNICAL PAPERS

Aerodynamic Blade Row Interactions in an Axial Compressor—Part I: Unsteady Boundary Layer Development

[+] Author and Article Information
Ronald Mailach, Konrad Vogeler

Dresden University of Technology, Institute for Fluid Mechanics, 01062 Dresden, Germany

J. Turbomach 126(1), 35-44 (Mar 26, 2004) (10 pages) doi:10.1115/1.1649741 History: Received December 01, 2002; Revised March 01, 2003; Online March 26, 2004
Copyright © 2004 by ASME
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References

Figures

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Sectional drawing of Dresden LSRC
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Surface-mounted hot-film array on a stator blade of first stage, suction side, midspan
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Rotor blade wake structure and effect on boundary layer of a stator blade in a compressor
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Flow field parameters upstream stator 1, middle of axial gap between rotor and stator, midspan, design point
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Parameters of the boundary layer, stator 1, suction side, midspan, 33% of chord length, design point (ξ=1.0)
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(a–c) Parameters of BL, (d) zones of BL (from Figs. 6 (a–c)), stator 1, suction side, midspan, design point (ξ=1.0)
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Skewness along the centerline of wake path (CL) and a path starting between the wakes, stator 1, suction side, midspan, design point (ξ=1.0)
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Comparison of raw data and ensemble-averaged data, stator 1, suction side, midspan, 41% of chord length, design point (ξ=1.0)
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(a) Boundary layer development (skewness), (b) zones of BL (from Fig. 9 (a)), stator 1, suction side, midspan, operating point near the stability limit for design speed (ξ=0.85)
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Parameters of boundary layer, stator 1, pressure side, midspan, design point (ξ=1.0)
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Boundary layer development, stator 1, pressure side, midspan, 23% of chord length, design point (ξ=1.0)

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