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TECHNICAL PAPERS

Viscous-Flow Two-Dimensional Analysis Including Secondary Flow Effects

[+] Author and Article Information
Reinhard Mönig, Frank Mildner

Siemens AG Power Generation KWU Mülheim a. d. Ruhr, Germany

Ralf Röper

B&B-AGEMA GmbH Aachen, Germany

J. Turbomach 123(3), 558-567 (Feb 01, 2000) (10 pages) doi:10.1115/1.1370167 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Adkins, G. G., and Smith, L. H., “Spanwise Mixing in Axial-Flow Turbomachines,” ASME-Paper 81-GT-57.
Gallimore,  S. J., 1986, “Spanwise Mixing in Multistage Axial Flow Compressors: Part II—Throughflow Calculations Including Mixing,” ASME J. Turbomach., 108, No. 1, pp. 10–16.
Howard, M. A., and Gallimore S. J., 1992, “Viscous Throughflow Modelling for Multi-stage Compressor Design,” ASME-Paper 92-GT-302, Cologne, Germany.
Edited by Johnsen, I. A., and Bullock, R. O., “Aerodynamic Design of Axial Flow Compressors”, NASA Report SP-36, 1965.
Schlichting, H., 1997, “Grenzschicht-Theorie,” 9th Ed. Springer-Verlag.
Hoynacki, A., 1999, “Einfluß von instationärer Strömung und Turbulenz auf die Grenzschichten und auf die Druckverteilungen von Beschaufelungen moderner mehrstufiger Axialverdichter,” Forschungsvereinigung Verbrennungskraftmaschinen (FVV) Abschlußbericht, Heft 679.
Roberts,  W. B., Serovy,  G. K., and Sandercock,  D. M., 1988, “Design Point Variation of Three-Dimensional Loss and Deviation for Axial Compressor Middle Stage,” ASME J. Turbomach., 110, pp. 426–433.
Hobbs,  D. E., and Weingold,  H. D., 1984, “Development of Controlled Diffusion Airfoils for Multistage Compressor Application,” ASME J. Eng. Gas Turbines Power, 106, pp. 271–278.
Janssen, M., Zimmermann, H., Kopper, F., and Richardson, J., 1995, “Application of Aero-Engine Technology to Heavy Duty Gas Turbines,” ASME-Paper 95-GT-133, Houston, Texas.
Elmendorf, W., Mildner, F., Röper, R., Krüger, U., and Kluck, M., 1998, “Three-Dimensional Analysis of a Multistage Compressor Flow Field,” ASME-Paper 98-GT-249, Stockholm, Sweden.
Tascflow 3D Documentation, 1995–1997, Advanced Scientific Computing Ltd., Waterloo, Ontario, Canada.
Köller, U., Mönig, R., Schreiber, H. A., and Küsters, B., 1999, “Development of Advanced Compressor Airfoils for HeavyDuty Gas Turbines; Part I: Design and Optimization,” ASME-Paper 99-GT-95, Indianapolis.

Figures

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Velocity distributions in boundary layers
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Numerical sublayer thickness for accelerated flows
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Numerical sublayer thickness for decelerated flows
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Model of axial compressor stage with shrouded hub and seal strips
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Compressor cross section three-stage research compressor (Institute for Jet Propulsion and Turbomachinery, Technical University of Aachen)
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Relative whirl angle downstream Rotor 1
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Relative whirl angle downstream Rotor 3
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Absolute whirl angle upstream Stator 1
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Absolute whirl angle upstream Stator 2
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Exit absolute whirl angle (three-stage research compressor)
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Stagnation pressure at compressor exit (three-stage research compressor)
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Relative whirl angle of a rotor in the mid section of the V84.3A compressor
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Relative whirl angle of a rotor at the back end of the V84.3A compressor
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Development of radial total pressure distribution of the V84.3A compressor
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Total temperature rotor 7
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Relative whirl angle rotor 7
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Total temperature rotor 8
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Relative whirl angle rotor 8

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