Implementation Methods of Wall Functions in Cell-vertex Numerical Solvers

Jaegle, F.; Cabrit, Olivier; Mendez, Simon; Poinsot, Thiérry

doi:10.1007/s10494-010-9276-1

Cited by 30 publications

(19 citation statements)

References 26 publications

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“…Inlet and outlet boundary conditions are based on the NavierStokes characteristic boundary condition (NSCBC) method [21]. Solid boundaries are modeled using logarithmic wall laws [22]. The gaseous solver can be combined with two different modules for the dispersed, liquid phase.…”

Section: Methodsmentioning

confidence: 99%

Eulerian and Lagrangian spray simulations of an aeronautical multipoint injector

Jaegle¹,

Senoner²,

García³

et al. 2011

Proceedings of the Combustion Institute

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Section: Methodsmentioning

confidence: 99%

Eulerian and Lagrangian spray simulations of an aeronautical multipoint injector

Jaegle¹,

Senoner²,

García³

et al. 2011

Proceedings of the Combustion Institute

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“…The boundary condition at the shaft is defined as wall slip. On the blade, two boundary conditions are used: no slip and log-law slip model (Jaegle et al, 2010). On the other walls, the log-law slip model is applied for all cases.…”

Section: Lesmentioning

confidence: 99%

CFD Modeling of a Realistic Turbofan Blade for Noise Prediction. Part 1: Aerodynamics

Arroyo¹,

Kholodov²,

Sanjosé³

et al. 2019

Proceedings of Global Power &Amp; Propulsion Society

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Various aspects of the numerical modeling of a scale-model turbofan blade are investigated for the purpose of future noise assessment. The fan geometry considered is the baseline configuration of the "Fan Noise Source Diagnostic Test" (SDT) experimental setup. Both Reynolds Averaged Navier-Stokes (RANS) simulations and Large Eddy Simulations (LES) are performed for a single rotor blade without the stator vanes and compared against the full configuration from previous works. With RANS simulations the mesh convergence is systematically studied. In the LES, two wall models and two numerical schemes are considered to evaluate the sensitivity of the boundary-layer transition to turbulence on the blade suction side. The different LES results are compared with the RANS solutions obtained using fully turbulent and transitional turbulence models. All RANS results show similar performance, whereas in the LES the no-slip wall condition gives better performance than the log-law slip wall condition. The prism layers on the hub and the shroud change the boundary layer profile upstream of the blade but do not affect the performance. On the blade, the RANS simulations show a laminar recirculation bubble whereas the LES exhibit a leading-edge vortex spiralling radially. The transitional RANS turbulence model gives the best agreement with the LES on the pressure side. The LES results are more affected by the mesh resolution than by the wall model or the numerical scheme, especially in the tip. In the wake all results show a good agreement with the experiment. Nomenclature Variables y + Dimensionless wall distance τ w Wall shear stress C p = P−P ∞ 0.5ρ ∞ U 2 ∞ Mean pressure coefficient C f = τ w 0.5ρU ∞ Mean skin friction coefficient U Mean velocity P Mean pressure Indices w Wall quantity ∞ Free-flow quantity t Total (stagnation) quantity This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License CC-BY-NC-ND 4.0

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“…These waves propagate and impact the neighboring blades. For Case 2, this interaction leads to the creation of a small separation zone close to the trailing edge of the stator around mid-span, which is a known sensitivity of the wall-law combined with non-intrusive SGS models in near wall regions [40]. Case 3 appears to be the least intrusive behind the stator blade, hence permitting a clearer representation of the vortex shedding.…”

Section: Effects Of the Sub-grid Scale Modelmentioning

confidence: 98%

Large Eddy Simulation of a High Pressure Turbine Stage: Effects of Sub-Grid Scale Modeling and Mesh Resolution

Papadogiannis

Duchaine

Sicot

et al. 2014

Volume 2B: Turbomachinery

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The use of Computational Fluid Dynamics (CFD) tools for integrated simulations of gas turbine components has emerged as a promising way to predict undesired component interactions thereby giving access to potentially better engine designs and higher efficiency. In this context, the ever-increasing computational power available worldwide makes it possible to envision integrated massively parallel combustion chamber-turbomachinery simulations based on Large-Eddy Simulations (LES). While LES have proven their superiority for combustor simulations, few studies have employed this approach in complete turbomachinery stages. The main reason for this is the known weaknesses of near wall flow modeling in CFD. Two approaches exist: the wall-modeled LES, where wall flow physics is modeled by a law-of-the-wall, and the wall-resolved LES where all the relevant near wall physics is to be captured by the grid leading to massive computational cost increases. This work investigates the sensitivity of wall-modeled LES of a high-pressure turbine stage. The code employed, called TurboAVBP, is an in-house LES code capable of handling turbomachinery configurations. This is possible through an LES-compatible approach with the rotor/stator interface treated based on an overset moving grids method. It is designed to avoid any interference with the numerical scheme, allow the proper representation of turbulent structures crossing it and run on massively parallel platforms. The simulations focus on the engine-representative MT1 transonic high-pressure turbine, tested by QinetiQ. To control the computational cost, the configuration employed is composed of 1 scaled stator section and 2 rotors. The main issues investigated are the effect of mesh resolution and the effect of sub-grid scale models in conjunction with wall modeling. The pressure profiles across the stator and rotor blades are in good agreement with the experimental data for all cases. Radial profiles at the rotor exit (in the near and far field) show improvement over RANS predictions. Unsteady flow features, inherently present in LES, are, however, found to be affected by the modeling parameters as evidenced by the obtained shock strengths and structures or turbulence content of the different simulations.

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Implementation Methods of Wall Functions in Cell-vertex Numerical Solvers

Cited by 30 publications

References 26 publications

Eulerian and Lagrangian spray simulations of an aeronautical multipoint injector

Eulerian and Lagrangian spray simulations of an aeronautical multipoint injector

CFD Modeling of a Realistic Turbofan Blade for Noise Prediction. Part 1: Aerodynamics

Large Eddy Simulation of a High Pressure Turbine Stage: Effects of Sub-Grid Scale Modeling and Mesh Resolution

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