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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Grahic Jump Location
(a–c) Parameters of BL, (d) zones of BL (from Figs. 6 (a–c)), stator 1, suction side, midspan, design point (ξ=1.0)
Grahic Jump Location
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)
Grahic Jump Location
Comparison of raw data and ensemble-averaged data, stator 1, suction side, midspan, 41% of chord length, design point (ξ=1.0)
Grahic Jump Location
(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)
Grahic Jump Location
Parameters of boundary layer, stator 1, pressure side, midspan, design point (ξ=1.0)
Grahic Jump Location
Boundary layer development, stator 1, pressure side, midspan, 23% of chord length, design point (ξ=1.0)
Grahic Jump Location
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
Grahic Jump Location
Flow field parameters upstream stator 1, middle of axial gap between rotor and stator, midspan, design point
Grahic Jump Location
Parameters of the boundary layer, stator 1, suction side, midspan, 33% of chord length, design point (ξ=1.0)



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