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TECHNICAL PAPERS

A Framework for Coupling Reynolds-Averaged With Large-Eddy Simulations for Gas Turbine Applications

[+] Author and Article Information
J. U. Schlüter, X. Wu, S. Kim, S. Shankaran, J. J. Alonso, H. Pitsch

Center for Turbulence Research and Aerospace Computing Lab, Stanford University, Stanford, CA 94305-3030

J. Fluids Eng 127(4), 806-815 (Feb 16, 2005) (10 pages) doi:10.1115/1.1994877 History: Received April 14, 2004; Revised February 16, 2005

Full-scale numerical prediction of the aerothermal flow in gas turbine engines are currently limited by high computational costs. The approach presented here intends the use of different specialized flow solvers based on the Reynolds-averaged Navier-Stokes equations as well as large-eddy simulations for different parts of the flow domain, running simultaneously and exchanging information at the interfaces. This study documents the development of the interface and proves its accuracy and efficiency with simple test cases. Furthermore, its application to a turbomachinery application is demonstrated.

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Copyright © 2005 by American Society of Mechanical Engineers
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Figures

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Figure 1

Computation of the flow path of an entire gas turbine: decomposition of the engine. Compressor and turbine with RANS; combustor with LES (combustor and turbine images from (34,5))

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Figure 2

Structure chart: exchange of root ranks needed for creation of intercommunicators

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Figure 3

Structure chart: initial handshake to establish direct communication between interface processors

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Figure 4

Structure chart: communication of flow data during flow computations

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Figure 5

Interface validation: geometry of the experimental test section (29)

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Figure 6

Interface validation: integrated RANS-LES of a confined jet

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Figure 7

Results of interface validation. Above: axial velocity profiles. Below: axial velocity fluctuations. Circles: experiments. Solid lines: LES with inflow from experimental data. Dashed lines: integrated RANS-LES, RANS with inflow from experimental data, LES inflow derived from simultaneously running RANS solver.

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Figure 8

Geometry for integrated LES/RANS computations: (a) full geometry, (b) reduced LES domain, and (c) schematic splitting of domain to two computational domains

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Figure 9

Integrated LES/RANS computations. Velocity components for different downstream positions. Circles: LES of full geometry (Fig. 8) dashed line: LES of expansion (Fig. 8) solid line: integrated LES-RANS computation (Fig. 8).

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Figure 10

Geometry of coupled NASA stage 35/prediffuser. RANS domain includes inflow channel, one rotor, and one stator. LES domain includes the diffuser. A 10deg axisymmetric sector is computed.

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Figure 11

Integrated RANS-LES of compressor/prediffuser: velocity distribution at the 50% plane

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Figure 12

Integrated RANS-LES of compressor/prediffuser: velocity distribution at the 50% plane. Close-up of the interface.

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Figure 13

Integrated RANS-LES of compressor/prediffuser: vorticity magnitude distribution at the 50% plane. Vorticity created on the surfaces of the stators can be found in the LES domain.

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