TY - GEN
T1 - High resolution numerical study on the coaxial supersonic turbulent flame structures
AU - Choi, Jeong Yeol
AU - Han, Sang Hoon
AU - Kim, Kyu Hong
AU - Yang, Vigor
N1 - Funding Information:
This work was supported by National Space Lab. Grant (NRF-2013M1A3A3A02042430) and Advanced Research Center Program (No. 2013073861) through the National Research Foundation of Korea(NRF) funded by the Ministry of Science, ICT and Future Planning of the Republic of Korea Government.
Publisher Copyright:
© 2014 by Jeong-Yeol Choi.
PY - 2014
Y1 - 2014
N2 - A diagnostic investigation regarding the turbulent combustion is analyzed for supersonic co-axial flame. The Mathematical formulation is based on the hybrid RANS/LES formulation for compressible reacting flows. A validation case study is performed for an experimental case with three levels of different grid system with three different high resolution schemes namely 3rd-order MUSCL scheme, a 5th-order WENO scheme and multi-dimensional 5th-order oMLP scheme. The time-averaged results of the experimental case shows the importance of fine grid resolution and high-order accurate numerical scheme for reliable prediction, capturing the fine scale instabilities of the supersonic turbulent combustion. The oMLP scheme exhibits a remarkable performance without a big expense. An analysis of the flow field is carried out to investigate the supersonic turbulent flame structure. The comparison of the combustion parameters including OH mass fraction, scalar dissipation rate and flame index reveals that the supersonic combustion of the validation case has a characteristics of turbulent lifted flame where the combustion is held mostly at premixed mode following turbulence mixing at the shear layer.
AB - A diagnostic investigation regarding the turbulent combustion is analyzed for supersonic co-axial flame. The Mathematical formulation is based on the hybrid RANS/LES formulation for compressible reacting flows. A validation case study is performed for an experimental case with three levels of different grid system with three different high resolution schemes namely 3rd-order MUSCL scheme, a 5th-order WENO scheme and multi-dimensional 5th-order oMLP scheme. The time-averaged results of the experimental case shows the importance of fine grid resolution and high-order accurate numerical scheme for reliable prediction, capturing the fine scale instabilities of the supersonic turbulent combustion. The oMLP scheme exhibits a remarkable performance without a big expense. An analysis of the flow field is carried out to investigate the supersonic turbulent flame structure. The comparison of the combustion parameters including OH mass fraction, scalar dissipation rate and flame index reveals that the supersonic combustion of the validation case has a characteristics of turbulent lifted flame where the combustion is held mostly at premixed mode following turbulence mixing at the shear layer.
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U2 - 10.2514/6.2014-3745
DO - 10.2514/6.2014-3745
M3 - Conference contribution
AN - SCOPUS:84913580945
T3 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
BT - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
Y2 - 28 July 2014 through 30 July 2014
ER -