TY - GEN
T1 - Parameters Analysis of Non-linear Combustion Instability Based on the Pulsed Trigger T-burner Technique
AU - Wei, Shao Juan
AU - Jin, Bing Ning
AU - Liu, Pei Jin
N1 - Publisher Copyright:
© 2018 IEEE.
PY - 2018/9/18
Y1 - 2018/9/18
N2 - High-amplitude pressure oscillation in solid propellant rocket motors shows nonlinear effects including the mean chamber pressure shift, limiting amplitudes of the acoustic oscillation, and energy transfer among acoustic modes. Along with the obvious undesirable vibrations, these features lead to the most damaging impact of combustion instability on system reliability and structural integrity. However, the physical mechanisms behind these phenomena and their effect on the propellant combustion and the acoustic oscillation behavior have never been successfully established. Therefore, fully understanding of the nonlinear combustion instability is crucial in the design process. In this paper, the nonlinear combustion instability parameters are obtained based on the pulse trigger T-burner technique and the relationship between the propellant combustion and the nonlinear acoustic oscillation is analyzed. Some different formulas of the composite propellants are adopted during the 30 pulsed T-burner firings. The operating pressures of tests are set at 7MPa and 10.5MPa, and the acoustic 1st mode frequencies are set at about 170Hz and 255Hz. The results show that: the propellant combustion has significant influences on the mean pressure shift (DC Shift) and the initial limit amplitude. Under the same trigger pressure, the mean pressure shift and the initial limit amplitude are significantly higher than those without propellant combustions. The DC Shift increases about 13.7~39.3%, and the initial limit amplitude increases about 23.6~47.4% under the same trigger pressure. The propellants with different formulas lead to different combustion response characteristics, and subsequently the initial limit oscillation. The higher Rp of the propellant is, the higher oscillation amplitude will be in the T-burner. Furthermore, the mean pressure shift is proportional to the combustion response value of the propellant and the square of the acoustic pressure oscillation amplitude.
AB - High-amplitude pressure oscillation in solid propellant rocket motors shows nonlinear effects including the mean chamber pressure shift, limiting amplitudes of the acoustic oscillation, and energy transfer among acoustic modes. Along with the obvious undesirable vibrations, these features lead to the most damaging impact of combustion instability on system reliability and structural integrity. However, the physical mechanisms behind these phenomena and their effect on the propellant combustion and the acoustic oscillation behavior have never been successfully established. Therefore, fully understanding of the nonlinear combustion instability is crucial in the design process. In this paper, the nonlinear combustion instability parameters are obtained based on the pulse trigger T-burner technique and the relationship between the propellant combustion and the nonlinear acoustic oscillation is analyzed. Some different formulas of the composite propellants are adopted during the 30 pulsed T-burner firings. The operating pressures of tests are set at 7MPa and 10.5MPa, and the acoustic 1st mode frequencies are set at about 170Hz and 255Hz. The results show that: the propellant combustion has significant influences on the mean pressure shift (DC Shift) and the initial limit amplitude. Under the same trigger pressure, the mean pressure shift and the initial limit amplitude are significantly higher than those without propellant combustions. The DC Shift increases about 13.7~39.3%, and the initial limit amplitude increases about 23.6~47.4% under the same trigger pressure. The propellants with different formulas lead to different combustion response characteristics, and subsequently the initial limit oscillation. The higher Rp of the propellant is, the higher oscillation amplitude will be in the T-burner. Furthermore, the mean pressure shift is proportional to the combustion response value of the propellant and the square of the acoustic pressure oscillation amplitude.
KW - combustion response
KW - DC Shift
KW - nonlinear combustion instability
KW - solid rocket motor
KW - T-burner
UR - http://www.scopus.com/inward/record.url?scp=85055492342&partnerID=8YFLogxK
U2 - 10.1109/ICMAE.2018.8467606
DO - 10.1109/ICMAE.2018.8467606
M3 - 会议稿件
AN - SCOPUS:85055492342
T3 - Proceedings of 2018 9th International Conference on Mechanical and Aerospace Engineering, ICMAE 2018
SP - 531
EP - 535
BT - Proceedings of 2018 9th International Conference on Mechanical and Aerospace Engineering, ICMAE 2018
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 9th International Conference on Mechanical and Aerospace Engineering, ICMAE 2018
Y2 - 10 July 2018 through 13 July 2018
ER -