The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part I: University Research and Methods Development

[+] Author and Article Information
Simon J. Gallimore, John J. Bolger, Nicholas A. Cumpsty, Mark J. Taylor, Peter I. Wright, James M. M. Place

Rolls-Royce Plc, Derby, DE24 8BJ U.K.

J. Turbomach 124(4), 521-532 (Nov 07, 2002) (12 pages) doi:10.1115/1.1507333 History: Received November 20, 2001; Online November 07, 2002
Copyright © 2002 by ASME
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Schematic diagram of zonal mixing length model
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Calibration of turbulence model with high-speed compressor characteristics
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Calibration of turbulence model with high-speed compressor interstage test data
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Comparison of experiment with CFD calculation for low-speed rotor exit flowfield
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Improved bleed hole modeling; (a) mesh, (b) contours of radial velocities on the casing (interval 10 m/s). Positive values indicate flow leaving the annulus.
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Definition of dihedral and sweep
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Computed near-suction surface axial velocity contours for datum and dihedral rotors
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Computed surface static pressure distributions for datum (2-D) and dihedral rotors
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Computed near-suction surface axial velocity contours for datum and swept rotors
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Computed surface static pressure distributions for datum (2-D) and swept rotors
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Front views onto suction surface of 3-D stage
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Comparison of 2-D and modified 3-D stage performance characteristics
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Comparison of measured 2-D and 3-D blade row exit conditions at design point
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Comparison of measured 2-D and 3-D blade row exit conditions at a near-stall operating point




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