Turbofan Broadband Noise Prediction Using the Lattice Boltzmann Method

The present work describes a numerical reproduction of the 22-in source diagnostic test fan rig of the NASA Glenn Research Center. Numerical flow simulations are performed for three different rotor/stator configurations and one rotational speed, representative of an approach operating condition, by...

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Bibliographic Details
Published in:AIAA journal 2018-02, Vol.56 (2), p.609-628
Main Authors: Casalino, D, Hazir, A, Mann, A
Format: Article
Language:English
Subjects:
Acoustic noise
Acoustic treatment
Broadband
Computational fluid dynamics
Computer simulation
Diagnostic systems
Flow simulation
Honeycomb construction
Mathematical analysis
Noise
Noise prediction
Research facilities
Rotor blades
Rotors
Stators
Turbofans
Variation
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Summary:The present work describes a numerical reproduction of the 22-in source diagnostic test fan rig of the NASA Glenn Research Center. Numerical flow simulations are performed for three different rotor/stator configurations and one rotational speed, representative of an approach operating condition, by using the lattice-Boltzmann solver PowerFLOW. The full stage and nacelle geometries are considered, and results are compared to available measurements. Tripping the rotor blades results in a slightly more accurate noise prediction as a consequence of a more accurate prediction of the velocity fluctuations in the rotor wake over the whole blade span. Fourier circumferential analyses are performed for an intake and a bypass duct section with the intent of explaining the origin of some tonal noise components and comparing the present results to available literature results. Finally, the effects of adding an acoustic treatment in the intake is shown by directly resolving the unsteady flowfield in a single-degree-of-freedom honeycomb layer.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J055674