Wall-Modeled Large-Eddy Simulations of a Multistage High-Pressure Compressor

Laborderie, Jerome de; Duchaine, Florent; Gicquel, Laurent; Moreau, Stéphane

doi:10.1007/s10494-019-00094-0

Cited by 5 publications

(4 citation statements)

References 58 publications

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“…The code AVBP [21] is used for the compressible LES. It has been extensively validated against multiple turbomachinery cases, including both aerodynamic and aeroacoustic ones [6,7,20,22]. The Taylor-Galerkin scheme TTG4A [23] that is 3rd order accurate in space and 4th order in time is used.…”

Section: Numerical Modelmentioning

confidence: 99%

Identification of Noise Sources in a Realistic Turbofan Rotor Using Large Eddy Simulation

Kholodov

Moreau

2020

Acoustics

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Large Eddy Simulation is performed using the NASA Source Diagnostic Test turbofan at approach conditions (62% of the design speed). The simulation is performed in a periodic domain containing one fan blade (rotor-alone configuration). The aerodynamic and acoustic results are compared with experimental data. The dilatation field and the dynamic mode decomposition (DMD) are employed to reveal the noise sources around the rotor. The trailing-edge radiation is effective starting from 50% of span. The strongest DMD modes come from the tip region. Two major noise contributors are shown, the first being the tip noise and the second being the trailing-edge noise. The Ffowcs Williams and Hawkings’ (FWH) analogy is used to compute the far-field noise from the solid surface of the blade. The analogy is computed for the full blade, for its tip region (outer 20% of span) and for lower 80% of span to see the contribution of the latter. The acoustics spectrum below 6 kHz is dominated by the tip part (tip noise), whereas the rest of the blade (trailing-edge noise) contributes more beyond that frequency.

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Section: Numerical Modelmentioning

confidence: 99%

Identification of Noise Sources in a Realistic Turbofan Rotor Using Large Eddy Simulation

Kholodov

Moreau

2020

Acoustics

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“…AVBP is a massively parallel code that solves the compressible Navier-Stokes equations on unstructured hybrid meshes. It is dedicated to unsteady compressible flows in complex geometries with or without combustion and is thus very suitable for turbomachinery flows (Dombard et al, 2020, de Laborderie et al, 2020. In the following, wall-resolved LES are produced to finely capture the flow behaviour near walls and capture features such as boundary layer separation, transition, etc (Segui et al, 2017, Dupuy et al, 2020.…”

Section: Numerical Approach and Modelingmentioning

confidence: 99%

Analysis of rotor/stator interactions in a high-speed low-pressure turbine cascade using Large-Eddy Simulations.

Boudin,

Dombard,

Duchaine

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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Turbomachinery flows are highly turbulent and prone to different types of instabilities. In low-pressure turbines (LPT), the wakes from the upstream bladerows provide the dominant source of unsteadiness. For Reynolds numbers at which LPT are generally operating, the majority of the blade boundary layer remains laminar. As a matter of fact, the suction side boundary layer of such flow is responsible for most of the efficiency loss. It is thus crucial to master the impact of the incoming wake turbulence and its effect on the transition of this boundary layer to master the generated losses. Such a rotor/stator interaction in new generation of low-pressure turbines, with the particularity of being locally transonic, is addressed numerically in this work. The considered geometry consists in a linear blade cascade in front of which bars rotate, acting as wake generators that periodically impact the blades leading edges, thereby influencing the aerodynamics of the cascade. For this study, Large-Eddy Simulations (LES) are carried out and compared to experimental results acquired at the Von Karman Institute during the Cleansky project SPLEEN. This paper investigates the interactions between the periodically incoming wakes and the turbine cascade. The transition of the suction side boundary layer, the pressure side separation bubble and the wall shear stress on the blade surface are specifically analysed along with the temporal evolution of the sonic pocket.

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“…To balance computation accuracy and cost, wall-modelled large eddy simulation (WMLES) has been developed in the past decades, with special attention paid to turbomachinery applications. These include WMLES for airfoils [6][7][8][9], compressor and turbine cascades [10,11], separation and transition [12], film cooling [13,14] and rotating flows [15].…”

Section: Introductionmentioning

confidence: 99%

Advanced Modeling of Flow and Heat Transfer in Rotating Disk Cavities Using Open-Source Computational Fluid Dynamics

Wang,

Gao,

Chew

et al. 2024

Journal of Engineering for Gas Turbines and Power

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Code_Saturne, an open-source computational fluid dynamics (CFD) code, has been applied to a range of problems related to turbomachinery internal air systems. These include a closed rotor-stator disc cavity, a co-rotating disc cavity with radial outflow and a co-rotating disc cavity with axial throughflow. Unsteady Reynolds-averaged Navier-Stokes (RANS) simulations and large eddy simulations (LES) are compared with experimental data and previous direct numerical simulation (DNS) and LES results. The results demonstrate Code_Saturne's capabilities for flow and heat transfer in rotating disc cavity flows. The Boussinesq approximation was implemented into the code for modelling centrifugally buoyant flow and heat transfer in the rotating cavity with axial throughflow. This development is validated using recent experimental data and CFD results. Good agreement is found between LES and RANS modelling in some cases, but for the axial throughflow cases, advantages of LES compared to URANS are significant for a high Reynolds number condition. The wall-modelled large eddy simulation (WMLES) method is recommended for balancing computational accuracy and cost in engineering applications.

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Wall-Modeled Large-Eddy Simulations of a Multistage High-Pressure Compressor

Cited by 5 publications

References 58 publications

Identification of Noise Sources in a Realistic Turbofan Rotor Using Large Eddy Simulation

Identification of Noise Sources in a Realistic Turbofan Rotor Using Large Eddy Simulation

Analysis of rotor/stator interactions in a high-speed low-pressure turbine cascade using Large-Eddy Simulations.

Advanced Modeling of Flow and Heat Transfer in Rotating Disk Cavities Using Open-Source Computational Fluid Dynamics

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