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Research Papers

An Approach for Inclusion of a Nonlocal Transition Model in a Parallel Unstructured Computational Fluid Dynamics Code

[+] Author and Article Information
Dragan Kožulović1

Institute of Propulsion Technology, DLR–German Aerospace Center, Cologne D-51147, Germanydragan.kozulovic@dlr.de

B. Leigh Lapworth

Aerothermal Methods Group, Rolls-Royce plc., Derby DE24 8BJ, UK

1

Present address: Institute of Fluid Mechanics, Technische Universität Braunschweig, Germany.

J. Turbomach 131(3), 031008 (Apr 08, 2009) (7 pages) doi:10.1115/1.2987238 History: Received August 11, 2007; Revised March 14, 2008; Published April 08, 2009

The implementation of an integral transition model in a parallel unstructured computational fluid dynamics code is described. In particular, an algorithm for gathering the nonlocal boundary layer values (momentum thickness and shape factor) from parallel distributed computational domains is presented. Transition modeling results are presented for a flat plate and for a low pressure turbine, covering a large variation of Reynolds numbers, Mach numbers, turbulence intensities, and incidence angles. Contrary to fully turbulent simulations, transitional predictions are in very good agreement with measurements. Furthermore, the computational overhead of transitional simulations is only 7% for one multigrid cycle.

Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 12

Influence of turbulence intensity Tu on the loss coefficient ζ

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Figure 13

Influence of Mach number M2th on the loss coefficient ζ

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Figure 11

Momentum thickness θ of transitional simulations at different Reynolds numbers, suction side

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Figure 15

Influence of incidence angle i on the loss coefficient ζ

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Figure 10

Shape factor H12 of transitional simulations at different Reynolds numbers, suction side

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Figure 9

Pressure distributions at different Reynolds numbers

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Figure 8

Influence of Reynolds number Re on the loss coefficient ζ

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Figure 7

Geometry and computational domain of the T106A low pressure turbine

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Figure 6

Skin friction coefficient cf of T3 flat plate series

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Figure 5

Circumferentialy averaged total pressure at outflow boundary, T106A turbine

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Figure 4

Root mean square residual from all five Navier–Stokes equations, T106A turbine

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Figure 3

Transition lines

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Figure 2

Intermittency γ of separation-induced transition

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Figure 1

Splitting of the boundary layer by domain decomposition

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Figure 14

Pressure distribution at large Mach number

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