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TECHNICAL PAPERS: Advanced Energy Systems

Numerical Simulation of Real-Gas Flow in a Supersonic Turbine Nozzle Ring

[+] Author and Article Information
J. Hoffren

Laboratory of Aerodynamics, Helsinki University of Technology, P.O. Box 4400, FIN-02105 HUT, Finland

T. Talonpoika, J. Larjola

Department of Energy Technology, Lappeenranta University of Technology, P.O. Box 20, FIN-53850 Lappeenranta, Finland

T. Siikonen

Laboratory of Applied Thermodynamics, Helsinki University of Technology, P.O. Box 4400, FIN-02105 HUT, Finland

J. Eng. Gas Turbines Power 124(2), 395-403 (Mar 26, 2002) (9 pages) doi:10.1115/1.1423320 History: Received March 01, 2000; Revised March 01, 2000; Online March 26, 2002
Copyright © 2002 by ASME
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References

Figures

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Relations for the calculation of the specific enthalpy of the superheated vapor hg using the enthalpies of the saturated vapor hgs and the ideal gas vapor hId
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The compressibility factor Zg is obtained by modifying a linear approximation for compressibility at temperature T/Tcr=5 with a correction ΔZ depending on the compressibility factor of the saturated vapor Zs
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(a) The original definition array and (b) the formed regular computational array for pressure. The dashed line defines the envelope of the real physical data.
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Grid for a passage between the turbine stator vanes. The flow is from lower left to upper right.
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(a) Inflow and (b) outflow conditions of the turbine stator passage nondimensionalized by the throat values
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(a) Mach number (b) density, (c) pressure, and (d) temperature distributions in the turbine stator. The nondimensional contour interval is 0.1 in the Mach plot, 0.01 in the density and pressure plots, and 0.02 in the temperature plot.
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Radial turbine design considered, shown by a coarse grid

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