Computational Modeling of Turbulent Spray Combustion Process Using RANS and Large-Eddy Simulations
Publication: Journal of Aerospace Engineering
Volume 35, Issue 1
Abstract
Computational fluid dynamics is applied to reproduce the characteristics of the liquid methanol burner presented by the National Institute of Standards and Technology (NIST). Reynolds average Navier-Stokes (RANS) and large-eddy simulations (LES) are employed, along with the steady nonadiabatic flamelets combustion model (using an extended reaction mechanism). The spray is not directly simulated, but instead, the linearized instability sheet atomization (LISA) model is implemented. The results obtained with RANS are used to estimate the scales of turbulence and design a mesh suitable for LES. The velocity field, spray characteristics, temperature, and combustion products are compared against the experimental data reported in the literature. Both simulations show similar results, differing mainly in the spray characteristics (size of the injected droplets). This seems to be related to the parameters of the Rosin-Rammler distribution used by the LISA model. Although a fraction of the spray evaporates downstream of the reaction zone, the fraction of unburned fuel is underestimated, which is expected considering the assumption of infinitely fast reaction. There is no formation of a vortex breakdown nor strong recirculation zone in the flow (due to the relatively low swirl number); nevertheless, some coherent structures are reproduced, showing the capacity of LES to capture the bigger scales of turbulence.
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Data Availability Statement
All data, models, and code generated or used during the study appear in the published article. Some or all data, models, or code generated or used during the study are available in a repository online in accordance with funder data retention policies: www-s.nist.gov/srmors/view_msds.cfm?srm=1837.
Acknowledgments
The authors gratefully acknowledge the financial support by CONACyT-AEM (BS-66085) and Cathedra’s CONACyT (2321) projects; they also acknowledge the computational support by TESE-SEP-TecNM 2018 program and GINPAC from the MCIAE SEPI-ESIME TICOMAN IPN for Aerodynamic laboratory assistance.
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Published In
Journal of Aerospace Engineering
Volume 35 • Issue 1 • January 2022
Copyright
© 2021 American Society of Civil Engineers.
History
Received: Feb 8, 2021
Accepted: Jul 26, 2021
Published online: Oct 8, 2021
Published in print: Jan 1, 2022
Discussion open until: Mar 8, 2022
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