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Journal of Turbomachinery | Volume 131 | Issue 4 | Research Paper
Research Papers

Sensitization of the SST Turbulence Model to Rotation and Curvature by Applying the Spalart–Shur Correction Term

[+] Author and Article Information
Pavel E. Smirnov

 New Technologies and Services, Dobrolyubov Avenue 14, 197198 St.-Petersburg, Russiapavel.smirnov@nts-int.spb.ru

Florian R. Menter

 ANSYS/CFX Germany, Staudenfeldweg 12, 83624 Otterfing, Germanyflorian.menter@ansys.com

J. Turbomach 131(4), 041010 (Jul 02, 2009) (8 pages) doi:10.1115/1.3070573 History: Received August 21, 2008; Revised October 07, 2008; Published July 02, 2009
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A rotation-curvature correction suggested earlier by Spalart and Shur (1997, “On the Sensitization of Turbulence Models to Rotation and Curvature  ,” Aerosp. Sci. Technol., 1(5), pp. 297–302) for the one-equation Spalart–Allmaras turbulence model is adapted to the shear stress transport model. This new version of the model (SST-CC) has been extensively tested on a wide range of both wall-bounded and free shear turbulent flows with system rotation and/or streamline curvature. Predictions of the SST-CC model are compared with available experimental and direct numerical simulations (DNS) data, on the one hand, and with the corresponding results of the original SST model and advanced Reynolds stress transport model (RSM), on the other hand. It is found that in terms of accuracy the proposed model significantly improves the original SST model and is quite competitive with the RSM, whereas its computational cost is significantly less than that of the RSM.
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Copyright © 2009 by American Society of Mechanical Engineers
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References

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+Developed channel flow at Re=5800; comparison with DNS of Kristoffersen and Anderrson (6)
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Developed channel flow at Re=5800; comparison with DNS of Kristoffersen and Anderrson (6)
Figure 1

Developed channel flow at Re=5800; comparison with DNS of Kristoffersen and Anderrson (6)

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+Developed channel flow at Re=5000, Ro=1.5; comparison with DNS of Lamballais (7)
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Developed channel flow at Re=5000, Ro=1.5; comparison with DNS of Lamballais (7)
Figure 2

Developed channel flow at Re=5000, Ro=1.5; comparison with DNS of Lamballais (7)

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+Developed flow in the curved channel; comparison with experiment of Wattendorf (8)
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Developed flow in the curved channel; comparison with experiment of Wattendorf (8)
Figure 3

Developed flow in the curved channel; comparison with experiment of Wattendorf (8)

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+Schematic of the flow geometry and grid for the U-turn flow of Monson (9)
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Schematic of the flow geometry and grid for the U-turn flow of Monson (9)
Figure 4

Schematic of the flow geometry and grid for the U-turn flow of Monson (9)

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+Turbulent flow in a duct with U-turn; comparison with experiment of Monson (9)
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Turbulent flow in a duct with U-turn; comparison with experiment of Monson (9)
Figure 5

Turbulent flow in a duct with U-turn; comparison with experiment of Monson (9)

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+Schematic of the hydro cyclone, computational domain, and positions of measurement planes (experiments of Hartley (10))
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Schematic of the hydro cyclone, computational domain, and positions of measurement planes (experiments of Hartley (10))
Figure 6

Schematic of the hydro cyclone, computational domain, and positions of measurement planes (experiments of Hartley (10))

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+Time-averaged profiles of the tangential velocity in the hydrocyclone; comparison with experiments of Hartley (10).
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Time-averaged profiles of the tangential velocity in the hydrocyclone; comparison with experiments of Hartley (10).
Figure 7

Time-averaged profiles of the tangential velocity in the hydrocyclone; comparison with experiments of Hartley (10).

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+General view of the compressor stage, reproduced from Ref. 11
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General view of the compressor stage, reproduced from Ref. 11
Figure 8

General view of the compressor stage, reproduced from Ref. 11

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+Total pressure ratio for the centrifugal compressor; comparison with the experiment of Ziegler (11)
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Total pressure ratio for the centrifugal compressor; comparison with the experiment of Ziegler (11)
Figure 9

Total pressure ratio for the centrifugal compressor; comparison with the experiment of Ziegler (11)

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+Computational domain and grid used for NACA 0012 wing with rounded tip (experiments of Chow (12))
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Computational domain and grid used for NACA 0012 wing with rounded tip (experiments of Chow (12))
Figure 10

Computational domain and grid used for NACA 0012 wing with rounded tip (experiments of Chow (12))

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+NACA 0012 wing with rounded tip: profiles of nondimensional cross flow and axial velocity components at three planes located downstream of the trailing edge; comparison with experiments of Chow (12)
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NACA 0012 wing with rounded tip: profiles of nondimensional cross flow and axial velocity components at three planes located downstream of the trailing edge; comparison with experiments of Chow (12)
Figure 11

NACA 0012 wing with rounded tip: profiles of nondimensional cross flow and axial velocity components at three planes located downstream of the trailing edge; comparison with experiments of Chow (12)

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+NACA 0012 wing with rounded tip (12): computed distributions of the axial velocity at the plane passing through the vortex core
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NACA 0012 wing with rounded tip (12): computed distributions of the axial velocity at the plane passing through the vortex core
Figure 12

NACA 0012 wing with rounded tip (12): computed distributions of the axial velocity at the plane passing through the vortex core

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+NACA 0012 wing with rounded tip (12): eddy viscosity ratio computed with the use of SST and SST-CC turbulence models
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NACA 0012 wing with rounded tip (12): eddy viscosity ratio computed with the use of SST and SST-CC turbulence models
Figure 13

NACA 0012 wing with rounded tip (12): eddy viscosity ratio computed with the use of SST and SST-CC turbulence models

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