Unsteady Interaction Between a Transonic Turbine Stage and Downstream Components

Davis, Roger L.; Yao, Jixian; Clark, John P.; Stetson, Gary M.; Alonso, Juan J.; Jameson, Antony; Haldeman, Charles W.; Dunn, Michael G.

doi:10.1115/gt2002-30364

Cited by 24 publications

(9 citation statements)

References 9 publications

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“…With adapted turbulence models, computations of entire turbo-machinery sections is feasible. 4 On the other hand, the flow in the combustor is characterized by detached flows, chemical reactions, and fuel spray. Experience shows that an unsteady approach such as LES has major advantages in predicting these flows.…”

Section: Introductionmentioning

confidence: 99%

Large-Eddy Simulation Inflow Conditions for Coupling with Reynolds-Averaged Flow Solvers

2004

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Hybrid approaches using a combination of Reynolds-averaged Navier-Stokes (RANS) approaches and large eddy simulations (LES) have become increasingly popular. One way to construct a hybrid approach is to apply separate flow solvers to components of a complex system and to exchange information at the interfaces of the domains. For the LES flow solver, boundary conditions then have to be defined on the basis of the Reynoldsaveraged flow statistics delivered by a RANS flow solver. This is a challenge, which also arises, for instance, when defining LES inflow conditions from experimental data. The problem for the coupled RANS-LES computations is further complicated by the fact that the mean flow statistics at the interface may vary in time and are not known a priori but only from the RANS solution. The present study defines a method to provide LES inflow conditions through auxiliary, a priori LES computations, where an LES inflow database is generated. The database is modified to account for the unsteadiness of the interface flow statistics.

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Section: Introductionmentioning

confidence: 99%

Large-Eddy Simulation Inflow Conditions for Coupling with Reynolds-Averaged Flow Solvers

2004

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“…The quality of the computed results can only be guaranteed on the basis of the separate validation process that the component codes have undergone and the detailed testing of the interface routines that has been presented in previous work. Some validation studies of the individual flow solvers are given in Yao et al 8 and Davis et al 1,23 for the TFLO code and in Mahesh et al 24 and Constantinescu et al 2 for the CDP code. The interface has been developed and tested in detail over the last two years [14][15][16] .…”

Section: Integrated Rans-les Of a Compressor-prediffusermentioning

confidence: 99%

Integrated RANS-LES Computations in Gas Turbines: Compressor-Diffusor Coupling

Schlüter

Kim

et al. 2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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Multi-component effects, such as compressor-combustor interactions, are difficult to predict with computational fluid dynamics using reasonable computational resources due to the variety of physical phenomena, which have to be modeled. The approach described in the present study is to couple two separate flow solvers, a RANS flow solver computing the last stage of a compressor and an LES flow solver computing the prediffuser of a combustor. At the interface the flow solvers exchange the flow data in order to define each others boundary conditions at the interface plane. The use of multiple flow solvers allows the application of the most appropriate flow solver for each flow section. The present study describes the approach in general, the interface, which allows running multiple flow solvers, its validation, and presents its application to the compressor-diffuser example.

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“…This can be done efficiently by a flow solver based on the Reynolds-Averaged Navier-Stokes (RANS) approach. Using high-speed computers, it is currently possible to compute entire turbine sections [1] and the computation of entire comressor sections is matter of current investigations.…”

Section: Motivationmentioning

confidence: 99%

Towards Multi-Component Analysis of Gas Turbines by CFD: Integration of RANS and LES Flow Solvers

Schlüter

Pitsch

Moin

et al. 2003

Volume 1: Turbo Expo 2003

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NOMENCLATURE Variable names:x i cartesian coordinates (i = 1, 2, 3) u i velocity components (i = 1, 2, 3) in cartesian coordinates U x axial velocity component in cylindrical coodinates U φ azimuthal velocity component in cylindrical coodinates ρ density k turbulent kinetic energy ν t turbulent eddy viscosity t time using LES time-step ∆t τ time using RANS time-step ∆τ τ F body force time constant Subscripts: RANS RANS flow solver variables LES LES flow solver variables DB data base variables ABSTRACTThe numerical prediction of the entire aero-thermal flow through an entire gas turbine is currently limited by its high computational costs. The approach presented here intends to use several specialized flow solvers based on the Reynolds-averaged Navier-Stokes equations (RANS) as well as Large Eddy Simulations (LES) running simultaneously and exchanging information at the interfaces. This study documents the development of the interface and proves its accuracy and efficiency on simple testcases.

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Unsteady Interaction Between a Transonic Turbine Stage and Downstream Components

Cited by 24 publications

References 9 publications

Large-Eddy Simulation Inflow Conditions for Coupling with Reynolds-Averaged Flow Solvers

Large-Eddy Simulation Inflow Conditions for Coupling with Reynolds-Averaged Flow Solvers

Integrated RANS-LES Computations in Gas Turbines: Compressor-Diffusor Coupling

Towards Multi-Component Analysis of Gas Turbines by CFD: Integration of RANS and LES Flow Solvers

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