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Research Papers

Assessment of Various Turbulence Models in a High Pressure Ratio Centrifugal Compressor With an Object Oriented CFD Code

[+] Author and Article Information
Luca Mangani1

Ernesto Casartelli

 Lucerne University of Applied Sciences and Arts, Technik & Architektur, Technikumstrasse 21, Horw, 6048, Switzerland

Sebastiano Mauri

 Aerodynamics Compressors, MAN Diesel & Turbo Schweiz AG, Hardstrasse 319, Zuerich, 8005, Switzerland

1

Corresponding author.

J. Turbomach 134(6), 061033 (Sep 12, 2012) (10 pages) doi:10.1115/1.4006310 History: Received July 18, 2011; Revised July 28, 2011; Published September 12, 2012; Online September 12, 2012

The flow field in a high pressure ratio centrifugal compressor with a vaneless diffuser has been investigated numerically. The main goal is to assess the influence of various turbulence models suitable for internal flows with an adverse pressure gradient. The numerical analysis is performed with a 3D RANS in-house modified solver based on an object-oriented open-source library. According to previous studies from varying authors, the turbulence model is believed to be the key parameter for the discrepancy between experimental and numerical results, especially at high pressure ratios and high mass-flow. Particular care has been taken at the wall, where a detailed integration of the boundary layer has been applied. The results present different comparisons between the models and experimental data, showing the influence of using advanced turbulence models. This is done in order to capture the boundary layer behavior, especially in large adverse pressure gradient single stage machinery.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Overall centrifugal compressor domain

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Figure 2

Computational domain

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Figure 3

Computational grid for AWT turbulence model

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Figure 4

Modeled tip gap for AWT turbulence model

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Figure 5

Pressure ratio over mass-flow rate for three rotational speeds

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Figure 6

Efficiency over mass-flow rate for three rotational speeds

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Figure 7

Leading edge plane rotating Mach contours at design condition (AWT)

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Figure 8

Impeller exit rotating Mach contours at design condition (AWT)

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Figure 9

BLADE-TO-BLADE SECTION ROTATING MACH CON-TOURS AT DESIGN CONDITION (AWT)

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Figure 10

Contour plots of rotating Mach at 90% of span: 40,000 RPM

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Figure 11

Contour plots of rotating Mach at impeller exit: 40,000 RPM and M = 2.62

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Figure 12

70% span vectors and impeller exit contour maps: 30,000 RPM

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Figure 13

Impeller streamlines: 30,000 RPM

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