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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

Thygesen, R., 2000, “Optimization of Return Channel Blades for Radial Compressors,” von Karman Institute PR 2000–21, Sint-Genesius-Rode, Belgium.
Meng, S. Y., and Jackson, E. D., 1983, “The continuous Diffusion Crossover System Design,” ASME FED-Vol. 3, Return Passages of Multistage Turbomachinery.
Casey M., and Wintergerste T., 2000, “Best Practice Guidelines,” Ercoftac Special Interest Group on “Quality and Trust in Industrial CFD,” Ercoftac.
Sorokes, J., and Kopko, J., 2001, “Analytical and Test Experiences Using a Rib Diffuser in a High Flow Centrifugal Compressor Stage,” ASME 2001-GT-0320.
Ardizzon, G., and Pavesi, G., 2003, “Influence of the Stator/Rotor Interaction on Reverse Flow at Off-design Operation,” Proceedings of 5th European Conference on “Turbomachinery Fluid Dynamics and Thermodynamics,” Prague, pp. 619–628.
Lenke, L. J., and Simon, H., 1998, “Numerical simulation of the flow through the return channel of Mutltistage Centrifugal Compressors,” ASME 98-GT-255.
Lakhsminayarana, B., 1996, “Fluid Dynamics and Heat Transfer of Turbomachinery,” Wiley, New York.
Van den Braembussche, R. A., 1990, “Design and Optimization of Centrifugal Compressor,” von Karman Institute CN 141, Sint-Genesius-Rode, Belgium.
Rothstein, E., 1984, “Experimentelle und Theoretische Untersuchung der Strömungsvorgänge in Rückfürkanälen von Radialverdichterstufen insbesondere solchen mit geringen Kanalbreite,” Ph.D. thesis, RWTH Aachen, Germany.
Simon, H., and Rothstein, E., 1983, “On the Development of Return Passages of Multistage Centrifugal Compressors,” ASME FED-Vol. 3, Return Passages of Multistage Turbomachinery.
Demeulenaere, A., 1997, “Conception et development d’une methode inverse pour la generation d’aubes de turbomachines,” von Karman Institute, Ph.D thesis, Sint-Genesius-Rode, Belgium.
Demeulenaere,  A., and Van den Braembussche,  R. A., 1998, “Three-dimensional Inverse Method for Turbomachinery Blading Design,” ASME J. Turbomach., 120, pp. 247–255.
Veress, A., 2001, “Inverse Design on Return Flow Channel for Multistage Radial Compressor,” von Karman Institute PR 2001–27, Sint-Genesius-Rode, Belgium.

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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