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TECHNICAL PAPERS

A Solution Strategy Based on Segmented Domain Decomposition Multigrid for Turbomachinery Flows

[+] Author and Article Information
M. L. Celestina

A. P. Solutions, Inc., Cleveland, OH 44135e-mail: mark.celestina@grc.nasa.gov

J. J. Adamczyk

NASA Glenn Research Center, Cleveland, OH 44135

S. G. Rubin

University of Cincinnati, Cincinnati, OH 45221

J. Turbomach 124(3), 341-350 (Jul 10, 2002) (10 pages) doi:10.1115/1.1451085 History: Received January 30, 2001; Online July 10, 2002
Copyright © 2002 by ASME
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References

Celestina, M. L., 1999, “Segmented Domain Decomposition Multigrid for 3-D Turbomachinery Flows,” Ph.D. dissertation, University of Cincinnati, Cincinnati, OH.
Berger,  M. J., and Colella,  P., 1989, “Local Adaptive Mesh Refinement for Shock Hydrodynamics,” J. Comp. Phys.,82, pp. 64–84.
Steger,  J., and Benek,  J. A., 1987, “On the Use of Composite Grid Schemes in Computational Aerodynamics,” Comput. Methods Appl. Mech. Eng., 64, pp. 301–320.
Liou, M.-S., and Kao, K.-H., 1994, “Progress in Grid Generation: From Chimera to DRAGON Grid,” NASA TM 106709.
Brandt,  A., 1977, “Multi-Level Adaptive Solutions to Boundary-Value Problems,” Math. Comput., 31, 138, pp. 333–390.
Srinivasan,  K., and Rubin,  S. G., 1997, “Solution Based Grid Optimization Through Segmented Multigrid Domain Decomposition,” J. Comp. Phys.,136, pp. 467–493.
Adamczyk,  J. J., Celestina,  M. L., Beach,  T. A., and Barnett,  M., 1990, “Simulation of Three-Dimensional Viscous Flows Within a Multistage Turbine,” ASME J. Turbomach., 112, pp. 370–376.
Launder,  B. E., and Spalding,  D. B., 1974, “The Numerical Computation of Turbulent Flows,” Comput. Methods Appl. Mech. Eng., 3, pp. 269–289.
Shabbir, A., Zhu, J., and Celestina, M. L., 1996, “Assessment of Three Turbulence Models in a Compressor Rotor,” ASME 96-GT-198.
Mulac, R. A., 1986, “A Multistage Mesh Generator for Solving the Average-Passage Equation System,” NASA CR-179539.
Zierke, W. C., and Deutsch, S., 1989, “The Measurement of Boundary Layers on a Compressor Blade in Cascade, Vol. 1,” NASA CR-185118.
McFarland,  E. R., 1982, “Solution of Plane Cascade Flow Using Improved Surface Singularity Methods,” ASME J. Eng. Power, 104, pp. 668–674.
McFarland,  E. R., 1984, “A Rapid Blade-to-Blade Solution for Use in Turbomachinery Design,” ASME J. Eng. Gas Turbines Power, 106, pp. 376–382.
Arts, T., Lambert de Rouvroit, M., and Rutherford, A. W., 1990, “Aero-Thermal Investigation of a Highly Loaded Transonic Linear Turbine Guide Vane Cascade,” VKI Technical Note 174.

Figures

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Global parent mesh with two child meshes in computational coordinates. The dashed line depicts the boundaries of the child meshes.
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Resolution of blade surface definition with mesh refinement
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Schematic of a parent mesh/child mesh interface surface
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Schematic of SDDMG procedure
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Schematic of the ARL compressor cascade
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Sectional view of the ARL compressor SDDMG mesh at midspan with seven mesh levels
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SDDMG mesh near the leading edge region of the ARL compressor at midspan
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SDDMG mesh near the trailing edge region of the ARL compressor at midspan
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Contours of velocity magnitude at midspan
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Velocity vectors near the suction surface trailing edge midspan for SDDMG
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Convergence of blade surface Cp for all SDDMG mesh levels versus normalized distance from the leading edge at midspan
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Nondimensional axial velocity versus distance from the suction surface at midspan
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Comparison of blade surface Cp versus percent chord at midspan for experimental data and SDDMG
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Comparison of nondimensional axial velocity versus pitch at midspan for experimental data and SDDMG
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Schematic of VKI turbine cascade
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Sectional view of the VKI turbine SDDMG mesh at midspan with six mesh levels
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Mach number contours at midspan in increments of 0.05
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Flow vectors near the trailing edge at midspan
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Loss coefficient at 143 percent chord at midspan
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Nondimensional axial velocity versus distance from the suction surface at midspan
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Comparison of loss coefficient at 143 percent chord at midspan

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