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Research Papers: Flows in Complex Systems

Investigation of the Performance of Turbulence Models With Respect to High Flow Curvature in Centrifugal Compressors

[+] Author and Article Information
Shady Ali

Department of Mechanical and
Materials Engineering,
The University of Western Ontario,
London, ON N6A 5B9, Canada
e-mail: sali332@uwo.ca

Kevin J. Elliott

Department of Mechanical and
Materials Engineering,
The University of Western Ontario,
London, ON N6A 5B9, Canada
e-mail: kjameselliott@gmail.com

Eric Savory

Department of Mechanical and
Materials Engineering,
The University of Western Ontario,
London, ON N6A 5B9, Canada
e-mail: esavory@uwo.ca

Chao Zhang

Department of Mechanical and
Materials Engineering,
The University of Western Ontario,
London, ON N6A 5B9, Canada
e-mail: czhang3@uwo.ca

Robert J. Martinuzzi

Department of Mechanical and
Manufacturing Engineering,
University of Calgary,
Calgary, AB T2N 1N4, Canada
e-mail: rmartinu@ucalgary.ca

William E. Lin

Department of Mechanical and
Materials Engineering,
The University of Western Ontario,
London, ON N6A 5B9, Canada
e-mail: wlin26@uwo.ca

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received March 27, 2015; final manuscript received October 7, 2015; published online December 23, 2015. Assoc. Editor: Sharath S. Girimaji.

J. Fluids Eng 138(5), 051101 (Dec 23, 2015) (10 pages) Paper No: FE-15-1215; doi: 10.1115/1.4031779 History: Received March 27, 2015; Revised October 07, 2015

The goal of this research is to evaluate the performance of three turbulence models with respect to flow with high curvature in a centrifugal compressor stage designed for an aero-engine. The effectiveness of the curvature correction terms in the two-equation turbulence models is the main focus of this study, as implemented in the curvature-corrected shear stress transport (SST-CC) model of Smirnov and Menter. The SST-CC model uses a production multiplier in the k and ω equations. SST-CC results were compared against the SST model and previous simulations by Bourgeois et al. (2011, “Assessment of Turbulence Model Predictions for an Aero-Engine Centrifugal Compressor,” ASME J. Turbomach., 133(1), pp. 1–15) using the Reynolds stress model (RSM–SSG) for stage performance characteristics, experimental velocity profiles at the impeller–diffuser interface, and velocity contours at the diffuser exit. The production multiplier was investigated in the compressor impeller. The comparisons showed that the SST-CC model better predicted the choke region in the pressure characteristic and efficiency characteristic, whereas the SST model better predicted the stall region. However, both models predicted a similar mean flow velocity field. Analysis of the production multiplier demonstrated that the term provided the expected effects near the walls of the convex and concave surfaces. However, away from the walls where turbulent production term was insignificant, the production multiplier showed abnormal predictions. The rotation effects were found to be weaker than the curvature effects near the impeller trailing edge of the current compressor.

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References

Bourgeois, J. A. , Martinuzzi, R. J. , Savory, E. , Zhang, C. , and Roberts, D. A. , 2011, “ Assessment of Turbulence Model Predictions for an Aero-Engine Centrifugal Compressor,” ASME J. Turbomach., 133(1), p. 011025. [CrossRef]
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Roberts, D. A. , and Steed, R. , 2004, “ A Comparison of Steady State Centrifugal Stage CFD Analysis to Experimental Rig Data,” ANSYS User’s Conference, Pittsburgh, PA.
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Smirnov, P. , and Menter, F. , 2009, “ Sensitization of the SST Turbulence Model to Rotation and Curvature by Applying the Spalart-Shur Correction Term,” ASME J. Turbomach., 131(4), pp. 1–8. [CrossRef]
Moore, J. , Moore, J. G. , and Johnson, M. W. , 1977, “ On Three-Dimensional Flow in Centrifugal Impellers,” HM Stationery Office, London, C.P. No. 1384.
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Bourgeois, J. A. , 2008, “ Numerical Mixing Plane Studies With Validation for Aero-Engine Centrifugal Compressor Design,” Master of Engineering Science thesis, University of Western Ontario, London, ON.
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Figures

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Fig. 1

Geometry of the compressor stage

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Fig. 2

Centrifugal compressor computational domain

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Fig. 3

Pressure characteristic for the SST, SST-CC, and RSM–SSG models as compared to the experimental data. Thebars on the experimental points indicate experimental uncertainty.

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Fig. 4

Efficiency characteristic for the SST, SST-CC, and RSM–SSG models as compared to the experimental data. Thebars on the experimental points indicate experimental uncertainty.

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Fig. 5

Circumferential velocity at the mixing plane, normalized by blade tip speed. The bars on the experimental points indicate experimental uncertainty.

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Fig. 6

Radial velocity at the mixing plane, normalized by blade tip speed. The bars on the experimental points indicate experimental uncertainty.

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Fig. 7

Normalized axial velocity contours (ca) at the diffuser exit: (a) experimental data [1], (b) SST, (c) SST-CC, and (d)RSM–SSG [17]

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Fig. 8

Normalized circumferential velocity (cθ) contours at the diffuser exit: (a) experimental data [1], (b) SST, (c) SST-CC, and (d) RSM–SSG [17]

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Fig. 9

Streamwise planes and lines of interest and corresponding fr1 contours and radius of curvature component: (a) planes and lines shown on the impeller, (b) curvature of interest and corresponding fr1 at ξ = 0.21, (c) curvature of interest and corresponding fr1 at ξ = 0.65, and (d) curvature of interest and corresponding fr1 at ξ = 0.96

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Fig. 10

Profiles of turbulence production and production multiplier (a) along the circumferential direction at ξ = 0.21 and ζ = 0.5, (b) along the spanwise direction at ξ = 0.65 and θ = 0.5, and (c) along the circumferential direction at ξ = 0.96 and ζ = 0.5

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Fig. 11

Contours of r* and r̃ at planes: (a) and (b) ξ = 0.21, (c) and (d) ξ = 0.65, and (e) and (f) ξ = 0.96

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