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Research Papers

Large-Eddy Simulations of Wall Bounded Turbulent Flows Using Unstructured Linear Reconstruction Techniques

[+] Author and Article Information
Dario Amirante

Thermo-Fluid Systems UTC,
University of Surrey,
Guildford, Surrey GU2 7XH, UK
e-mail: d.amirante@surrey.ac.uk

Nicholas J. Hills

Thermo-Fluid Systems UTC,
University of Surrey,
Guildford, Surrey GU2 7XH, UK
e-mail: n.hills@surrey.ac.uk

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 5, 2014; final manuscript received August 6, 2014; published online November 18, 2014. Editor: Ronald Bunker.

J. Turbomach 137(5), 051006 (May 01, 2015) (11 pages) Paper No: TURBO-14-1196; doi: 10.1115/1.4028549 History: Received August 05, 2014; Revised August 06, 2014; Online November 18, 2014

Large-eddy simulations (LES) of wall bounded, low Mach number turbulent flows are conducted using an unstructured finite-volume solver of the compressible flow equations. The numerical method employs linear reconstructions of the primitive variables based on the least-squares approach of Barth. The standard Smagorinsky model is adopted as the subgrid term. The artificial viscosity inherent to the spatial discretization is maintained as low as possible reducing the dissipative contribution embedded in the approximate Riemann solver to the minimum necessary. Comparisons are also discussed with the results obtained using the implicit LES (ILES) procedure. Two canonical test-cases are described: a fully developed pipe flow at a bulk Reynolds number Reb = 44 × 103 based on the pipe diameter, and a confined rotor–stator flow at the rotational Reynolds number ReΩ = 4 × 105 based on the outer radius. In both cases, the mean flow and the turbulent statistics agree well with existing direct numerical simulations (DNS) or experimental data.

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References

Figures

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Fig. 1

Subelements Hi used in the definition of the control volume Vi. Vi=∪Hi, with the union extended to all Hi sharing the mesh node i. For clarity, only the front elements Hi are shown.

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Fig 2

Pipe flow: instantaneous axial velocity contours

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Fig. 3

Pipe flow: mean velocity radial profile

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Fig. 4

Pipe flow: mean velocity Vz+ as a function of (1 − r)+

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Fig. 5

Pipe flow: radial profile of the Reynolds shear stress

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Fig. 6

Pipe flow: radial profiles of turbulence intensities. Solid line: DNS; dashed line: present LES; red curves: streamwise velocity component; black curves: tangential velocity component; blue curves: radial velocity component.

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Fig. 7

Geometry of the rotor–stator cavity

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Fig. 8

Rotor–stator flow: radial velocity contours on the periodic surface

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Fig. 9

Rotor–stator flow: axial velocity contours on the periodic surface

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Fig. 10

Rotor–stator flow: positive isosurfaces of the Q-criterion. The set of spirals develops on the rotor.

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Fig. 11

Rotor–stator flow: mean profiles of tangential and radial velocity components at three radial locations. (a) Inner radius r*= 0.3, (b) midradius r*= 0.5, and (c) outer radius r*= 0.7.

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Fig. 12

Rotor–stator flow: mean profiles of the radial velocity component in the boundary layers. Upper figures: stator and lower figures: rotor.

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Fig. 13

Rotor–stator flow: mean profiles of the tangential velocity component in the boundary layers. Upper figures: stator and lower figures: rotor.

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Fig. 14

Grid convergence: mean profiles of the radial velocity component in the boundary layers. Upper figures: stator and lower figures: rotor.

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Fig. 15

Grid convergence: mean profiles of the tangential velocity component in the boundary layers. Upper figures: stator and lower figures: rotor.

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Fig. 16

Rotor–stator flow: mean profiles of the Reynolds stress components Rθθ and Rrr at three radial locations. (a) Inner radius r* = 0.3, (b) midradius r* = 0.5, and (c) outer radius r* = 0.7.

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Fig. 17

Rotor–stator flow: velocity profile in the stator boundary layer at r*= 0.5 and ratio between the SGS stress divergence and the numerical viscosity

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