TY - GEN
T1 - Analysis and calculation of chemical non-equilibrium turbulent flow in a scramjet nozzle
AU - Wang, X. Y.
AU - Xie, G. N.
AU - Sundén, B.
PY - 2009
Y1 - 2009
N2 - In this paper, 7-species, 8-step finite-rate chemical reaction models of the non-equilibrium flow in a scramjet single expansion ramp nozzle have been investigated numerically. Chemical reactions and mass transfer under various freestream Mach numbers and flight height conditions are performed by the RNG k-ε turbulence model. The fluid flow in the nozzle is analyzed under non-equilibrium chemical reactions and frozen flow conditions. It is shown that the total temperature is obviously increased while the total pressure is evidently decreased in the chemical non-equilibrium flow at certain inlet conditions. The mass fractions of H2 and O2 are decreased while that of H2O is increased, and the mass fraction of N 2 is almost identical throughout the whole reaction process. This indicates that combustion occurs in the nozzle, and the scramjet nozzle can supplement the combustion in a supersonic combustor so that the performance of the nozzle can be increased. It can be found that there are eddies in the chemical non-equilibrium flow because of the variations of the mass fractions of O2, H, O and OH. These eddies suggest that the variations of the mass fractions of O2, H, O and OH is non-monotonic. Although the flow is speeded up, the chemical reaction at the beginning part of the nozzle is faster than that downstream. The calculation shows that the non-equilibrium chemical reactions should always be considered in investigations of the flow and performance of scramjet nozzles.
AB - In this paper, 7-species, 8-step finite-rate chemical reaction models of the non-equilibrium flow in a scramjet single expansion ramp nozzle have been investigated numerically. Chemical reactions and mass transfer under various freestream Mach numbers and flight height conditions are performed by the RNG k-ε turbulence model. The fluid flow in the nozzle is analyzed under non-equilibrium chemical reactions and frozen flow conditions. It is shown that the total temperature is obviously increased while the total pressure is evidently decreased in the chemical non-equilibrium flow at certain inlet conditions. The mass fractions of H2 and O2 are decreased while that of H2O is increased, and the mass fraction of N 2 is almost identical throughout the whole reaction process. This indicates that combustion occurs in the nozzle, and the scramjet nozzle can supplement the combustion in a supersonic combustor so that the performance of the nozzle can be increased. It can be found that there are eddies in the chemical non-equilibrium flow because of the variations of the mass fractions of O2, H, O and OH. These eddies suggest that the variations of the mass fractions of O2, H, O and OH is non-monotonic. Although the flow is speeded up, the chemical reaction at the beginning part of the nozzle is faster than that downstream. The calculation shows that the non-equilibrium chemical reactions should always be considered in investigations of the flow and performance of scramjet nozzles.
KW - Chemical reaction
KW - Mass fraction, combustion copyright
KW - Non-equilibrium flow
UR - http://www.scopus.com/inward/record.url?scp=77953186561&partnerID=8YFLogxK
U2 - 10.1115/GT2009-59368
DO - 10.1115/GT2009-59368
M3 - 会议稿件
AN - SCOPUS:77953186561
SN - 9780791848821
T3 - Proceedings of the ASME Turbo Expo
SP - 91
EP - 96
BT - Proceedings of the ASME Turbo Expo 2009
T2 - 2009 ASME Turbo Expo
Y2 - 8 June 2009 through 12 June 2009
ER -