TY - JOUR
T1 - Combustion performance of several nanosilicon-based nanoenergetics
AU - Aaron Mason, B.
AU - Groven, Lori J.
AU - Son, Steven F.
AU - Yetter, Richard A.
N1 - Funding Information:
The authors wish to acknowledge the funding of Defense Threat Reduction Agency, Counter-WMD basic research program, grant number HDTRA1-08-1-0006. The authors would also like acknowledge Jose G. Archuleta and Edward L. Romero of Los Alamos National Laboratories for powder characterization, and also Blaine Asay and Bryce Tappan of Los Alamos National Laboratory for their insight and interest in this work. The authors acknowledge Kevin Y. Cho for assisting with the instrumented tube burns and CHEETAH 4.0 calculations, Cole Yarrington for his support and advice, and finally, the authors would also like acknowledge the technical and administrative staff of Zucrow Laboratories at Purdue University.
PY - 2013
Y1 - 2013
N2 - Silicon-based nanoenergetics have great potential due to silicon's good thermochemical properties, high active content, and surface modification potential. The combustion characteristics of several silicon-based nanoenergetics were studied by performing equilibrium calculations, initial screening tests, and instrumented burn tube experiments. Results of constant pressure equilibrium calculations predicting adiabatic combustion temperatures and volumetric gas production are shown and the mechanisms that produce these results are discussed. For 14 of the 19 Si/oxidizer systems studied, such as Si/perchlorate systems, the predicted maximum adiabatic combustion temperatures are about 3000 K. For the materials considered the highest predicted combustion temperature is for the Si/polytetrafluoroethylene system at 3531 K, whereas the Si/metal oxide systems are predicted to have adiabatic combustion temperatures ranging from 2282 to 2978 K. The dissociation of SiO2 to SiO was observed to limit predicted adiabatic combustion temperatures. Theoretical maximum gas production of the reactive Si composites ranged from 350 to 6500 cm3/g, with Si/NH4ClO4 producing the most gas and Si/Fe2O3 producing the least. Based on initial screening tests, the nanopowder systems Si/NaClO4 · H 2O, Si/KMnO4, Si/NH4ClO4, and Si/sulfur were chosen for loose powder burn tube experiments using Si nanopowder. Of the reactive composites studied, Si/NH4ClO4 yielded the fastest loose powder tube burning rate, which was about 530 m/s.
AB - Silicon-based nanoenergetics have great potential due to silicon's good thermochemical properties, high active content, and surface modification potential. The combustion characteristics of several silicon-based nanoenergetics were studied by performing equilibrium calculations, initial screening tests, and instrumented burn tube experiments. Results of constant pressure equilibrium calculations predicting adiabatic combustion temperatures and volumetric gas production are shown and the mechanisms that produce these results are discussed. For 14 of the 19 Si/oxidizer systems studied, such as Si/perchlorate systems, the predicted maximum adiabatic combustion temperatures are about 3000 K. For the materials considered the highest predicted combustion temperature is for the Si/polytetrafluoroethylene system at 3531 K, whereas the Si/metal oxide systems are predicted to have adiabatic combustion temperatures ranging from 2282 to 2978 K. The dissociation of SiO2 to SiO was observed to limit predicted adiabatic combustion temperatures. Theoretical maximum gas production of the reactive Si composites ranged from 350 to 6500 cm3/g, with Si/NH4ClO4 producing the most gas and Si/Fe2O3 producing the least. Based on initial screening tests, the nanopowder systems Si/NaClO4 · H 2O, Si/KMnO4, Si/NH4ClO4, and Si/sulfur were chosen for loose powder burn tube experiments using Si nanopowder. Of the reactive composites studied, Si/NH4ClO4 yielded the fastest loose powder tube burning rate, which was about 530 m/s.
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U2 - 10.2514/1.B34902
DO - 10.2514/1.B34902
M3 - Article
AN - SCOPUS:84892587205
SN - 0748-4658
VL - 29
SP - 1435
EP - 1444
JO - Journal of Propulsion and Power
JF - Journal of Propulsion and Power
IS - 6
ER -