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TECHNICAL PAPERS

Inverse Design and Optimization of a Return Channel for a Multistage Centrifugal Compressor

[+] Author and Article Information
Árpád Veress

Department of Aircraft and Ships, Budapest University of Technology and Economics, H-1111 Budapest, Sztoczek u. 6 J ép. 4.em. 426, Hungary

René Van den Braembussche

Turbomachinery and Propulsion Department, von Kármán Institute for Fluid Dynamics, Waterloose steenweg, 72, B-1640 Sint-Genesius-Rode, Belgium

J. Fluids Eng 126(5), 799-806 (Dec 07, 2004) (8 pages) doi:10.1115/1.1792258 History: Received October 14, 2002; Revised April 29, 2004; Online December 07, 2004
Copyright © 2004 by ASME
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References

Figures

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Typical multistage barrel compressor cross section (courtesy MAN-Turbo)
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Schematic view of meridional cross section of the compressor stage with geometry definitions.
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Return vane design by the method of Rothstein
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Radial velocity component on a grid surface near the suction side of the return vanes (reference geometry)
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Control surface for the analytical vane design method
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Flow angle distribution imposed at hub and shroud
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Meridional velocity component on a grid surface near the suction surface of the controlled blade loading vanes
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Mach number distribution on the initial blade at 12% blade height from hub and shroud
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Imposed (o) and calculated (+) Mach number distribution on the redesigned vane at 12% blade height from hub and shroud.
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Comparison between original (gray) and redesigned (+++) vanes
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Comparison between original (gray) and redesigned (line) vanes in the m,R*θ plane.
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Velocity vectors on the second grid surface near the suction side of the CBL blade (a) and inverse designed blade (b)
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Velocity vectors projected on a cross section near the vane trailing edge

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