Large Eddy Simulation of a scale-model turbofan for fan noise source diagnostic

A wall-modeled statistically converged Large Eddy Simulation (LES) of the turbulent flow in the NASA Source Diagnostic Test turbofan has been successfully performed for the first time. A good agreement with aerodynamic measurements is observed for both Reynolds Averaged Navier-Stokes and LES results...

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Bibliographic Details
Published in:Journal of sound and vibration 2019-04, Vol.445, p.64-76
Main Authors: Pérez Arroyo, Carlos, Leonard, Thomas, Sanjosé, Marlène, Moreau, Stéphane, Duchaine, Florent
Format: Article
Language:English
Subjects:
Acoustic analogy
Acoustic noise
Acoustics
Aeroacoustic
Aerodynamics
Boundary layer transition
Broadband
Computational fluid dynamics
Computer simulation
Diagnostic systems
Fan stage
Frequencies
Impingement
Large eddy simulation
Navier-Stokes equations
Reynolds averaged Navier-Stokes method
Secondary flow
Simulation
Stators
Suction
Turbofans
Turbomachinery
Turbulence
Turbulent flow
Vanes
Vibration
Vortices
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Summary:A wall-modeled statistically converged Large Eddy Simulation (LES) of the turbulent flow in the NASA Source Diagnostic Test turbofan has been successfully performed for the first time. A good agreement with aerodynamic measurements is observed for both Reynolds Averaged Navier-Stokes and LES results, although the LES provides better results in the tip regions where large coherent structures appear and no flow separation on the stator vanes is observed. In the LES the boundary layer naturally transition to turbulence on the blade suction side but remains quasi laminar over most of its pressure side. The rotor-wake turbulence yielding the stage broadband noise is then seen to be quasi isotropic. Transition on the downstream stator vanes is not triggered by the wake impingement but rather occurs at mid-chord. Finally, acoustics are investigated using both Ffowcs Williams & Hawkings' and Goldstein's analogies from the recorded LES noise source on the stator vanes. The latter analogy provides levels closer to the measurements especially at high frequencies, although the results are most likely still influenced by too coherent rotor tip secondary flow at low frequencies.
ISSN:0022-460X
1095-8568
DOI:10.1016/j.jsv.2019.01.005