TY - JOUR
T1 - Quantitative analysis of the carbon generation characteristics during Mg/CO2 combustion
T2 - Implications for suppressing carbon deposition
AU - Zhu, Xiaofei
AU - Li, Chao
AU - Wei, Ronggang
AU - Ao, Wen
AU - Guo, Yu
AU - Hu, Jiaming
AU - Yang, Jiangang
AU - Hu, Chunbo
N1 - Publisher Copyright:
© 2020
PY - 2020/8
Y1 - 2020/8
N2 - Carbon deposition can significantly reduce the working stability and specific impulse performance of magnesium/carbon dioxide (Mg/CO2) powder rocket engines; however, few studies have quantitatively analyzed carbon generation characteristics during the Mg/CO2 combustion process. Therefore, this study presents a quantitative analysis of the carbon generation characteristics and degree of heterogeneous reaction during Mg/CO2 combustion in a closed high-temperature furnace. The analytical methods used include elemental analysis (EA) and inductively coupled plasma-optical emission spectrometry (ICP-OES). Experimental results showed that increasing the ambient temperature and decreasing the particle size both effectively suppressed carbon generation through a heterogeneous reaction, which is discussed from a thermodynamic perspective. When the particle size was 5 μm, the degree of heterogeneous reaction increased from 16.2% to 26.6% as the ambient temperature decreased from 1573 K to 1173 K; and when the ambient temperature was 1573 K, the degree of heterogeneous reaction increased from 16.2% to 23.2% as the particle size increased from 5 μm to 160 μm. Excessive CO concentration on the surface of Mg particles resulted in a large amount of carbon deposition, along with an insufficient Mg burnout rate. The proportion of Mg in the two pretreated powder samples participating in the heterogeneous reaction is reduced by 41% and 52%, respectively, compared with that in the source powder. Moreover, the combustion performance of pretreated Mg powder is typically excellent in CO2 due to the micro-explosion phenomenon. These findings are expected to contribute to improved working stability and specific impulse performance of Mg/CO2 powder rocket engines intended for Mars exploration.
AB - Carbon deposition can significantly reduce the working stability and specific impulse performance of magnesium/carbon dioxide (Mg/CO2) powder rocket engines; however, few studies have quantitatively analyzed carbon generation characteristics during the Mg/CO2 combustion process. Therefore, this study presents a quantitative analysis of the carbon generation characteristics and degree of heterogeneous reaction during Mg/CO2 combustion in a closed high-temperature furnace. The analytical methods used include elemental analysis (EA) and inductively coupled plasma-optical emission spectrometry (ICP-OES). Experimental results showed that increasing the ambient temperature and decreasing the particle size both effectively suppressed carbon generation through a heterogeneous reaction, which is discussed from a thermodynamic perspective. When the particle size was 5 μm, the degree of heterogeneous reaction increased from 16.2% to 26.6% as the ambient temperature decreased from 1573 K to 1173 K; and when the ambient temperature was 1573 K, the degree of heterogeneous reaction increased from 16.2% to 23.2% as the particle size increased from 5 μm to 160 μm. Excessive CO concentration on the surface of Mg particles resulted in a large amount of carbon deposition, along with an insufficient Mg burnout rate. The proportion of Mg in the two pretreated powder samples participating in the heterogeneous reaction is reduced by 41% and 52%, respectively, compared with that in the source powder. Moreover, the combustion performance of pretreated Mg powder is typically excellent in CO2 due to the micro-explosion phenomenon. These findings are expected to contribute to improved working stability and specific impulse performance of Mg/CO2 powder rocket engines intended for Mars exploration.
KW - Carbon deposition
KW - CO
KW - Combustion
KW - Magnesium
KW - Mars exploration
KW - Powder rocket engine
UR - http://www.scopus.com/inward/record.url?scp=85086414065&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2020.105966
DO - 10.1016/j.ast.2020.105966
M3 - 文章
AN - SCOPUS:85086414065
SN - 1270-9638
VL - 103
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 105966
ER -