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Numerical Analysis of the Impact of the Interior Nozzle Geometry on Low Mach Number Jet Acoustics

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Abstract

The flow and acoustic fields of subsonic turbulent hot jets exhausting from three divergent nozzles at a Mach number M=0.12 based on the nozzle exit velocity are conducted using a hybrid CFD-CAA method. The flow field is computed by highly resolved large-eddy simulations (LES) and the acoustic field is computed by solving the acoustic perturbation equations (APE) whose acoustic source terms are determined by the LES. The LES of the computational domain includes the interior of the nozzle geometry. Synthetic turbulence is prescribed at the inlet of the nozzle to mimic the exit conditions downstream of the last turbine stage. The LES is based on hierarchically refined Cartesian meshes, where the nozzle wall boundaries are resolved by a conservative cut-cell method. The APE solution is determined on a block structured mesh. Three nozzle geometries of increasing complexity are considered, i.e., the flow and acoustic fields of a clean geometry without any built-in components, a nozzle with a centerbody, and a nozzle with a centerbody plus struts are computed. Spectral distributions of the LES based turbulent fluctuated quantities inside the nozzle and further downstream are analyzed in detail. The noise sources in the near field are noticeably influenced by the nozzle built-in components. The centerbody nozzle increases the overall sound pressure level (OASPL) in the near field with respect to the clean nozzle and the centerbody-plus-strut nozzle reduces it compared to the centerbody nozzle due to the increased turbulent mixing. The centerbody perturbed nozzle configurations generate a remarkable spectral peak at S t=0.56 which also occurs in the APE findings in the near field region. This tone is generated by large scale vortical structures shed from the centerbody. The analysis of the individual noise sources shows that the entropy term possesses the highest acoustic contribution in the sideline direction whereas the vortex sound source dominates the downstream acoustics.

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Acknowledgments

The research was funded from the European Community’s Seventh Framework Programme (FP7, 2007-2013) PEOPLE program under the grant agreement No. FP7-290042 (COPAGT project). The authors gratefully thank the Gauss Centre for Supercomputing (GCS) for providing computing time for a GCS Large-Scale Project on the GCS share of the supercomputer JUQUEEN [44] at the Jülich Supercomputing Centre (JSC) and High Perfomance Computing Center Stuttgart (HLRS). GCS is the alliance of the three national supercomputing centres HLRS (Universität Stuttgart), JSC (Forschungszentrum Jülich), and LRZ (Bayerische Akademie der Wissenschaften) in Germany, funded by the German Federal Ministry of Education and Research (BMBF) and the German State Ministries for Research of Baden-Württemberg (MWK), Bayern (StMWFK) and Nordrhein-Westfalen (MIWF).

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Authors and Affiliations

  1. Institute of Aerodynamics, RWTH Aachen University, Wüllnerstraße 5a, 52062, Aachen, Germany

    Mehmet Onur Cetin, Seong Ryong Koh, Matthias Meinke & Wolfgang Schröder

  2. Forschungszentrum Jülich, JARA – High-Performance Computing, 52425, Jülich, Germany

    Matthias Meinke & Wolfgang Schröder

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  1. Mehmet Onur Cetin
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  2. Seong Ryong Koh
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  4. Wolfgang Schröder
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Correspondence to Mehmet Onur Cetin.

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Cetin, M.O., Koh, S.R., Meinke, M. et al. Numerical Analysis of the Impact of the Interior Nozzle Geometry on Low Mach Number Jet Acoustics. Flow Turbulence Combust 98, 417–443 (2017). https://doi.org/10.1007/s10494-016-9764-z

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  • DOI: https://doi.org/10.1007/s10494-016-9764-z

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