TY - GEN
T1 - A flamelet approach for modeling of liquid oxygen (LOX)/methane flames at supercritical pressures
AU - Zong, Nan
AU - Ribert, Guillaume
AU - Yang, Vigor
N1 - Copyright:
Copyright 2018 Elsevier B.V., All rights reserved.
PY - 2008
Y1 - 2008
N2 - A comprehensive theoretical/numerical framework has been established to treat the combustion of liquid oxygen (LOX) and methane under supercritical conditions. The model accounts for detailed LOX/methane reaction mechanisms, and accommodates the effect of scalar dissipation on finite-rate chemistry. Turbulence closure is achieved by a large-eddy simulation technique. Several different turbulent combustion models are implemented and assessed by comparing the chemical and turbulence time scales at conditions typical of liquid-propellant engine rocket operation. Results indicate that the flamelet assumption is appropriate. The direct-closure approach may over-predict the reaction rate. The supercritical mixing and combustion LOX and methane downstream of a splitter are analyzed systemically, and the effects of real-fluid thermodynamics on the cryogenic-fluid flame evolution are quantified.
AB - A comprehensive theoretical/numerical framework has been established to treat the combustion of liquid oxygen (LOX) and methane under supercritical conditions. The model accounts for detailed LOX/methane reaction mechanisms, and accommodates the effect of scalar dissipation on finite-rate chemistry. Turbulence closure is achieved by a large-eddy simulation technique. Several different turbulent combustion models are implemented and assessed by comparing the chemical and turbulence time scales at conditions typical of liquid-propellant engine rocket operation. Results indicate that the flamelet assumption is appropriate. The direct-closure approach may over-predict the reaction rate. The supercritical mixing and combustion LOX and methane downstream of a splitter are analyzed systemically, and the effects of real-fluid thermodynamics on the cryogenic-fluid flame evolution are quantified.
UR - http://www.scopus.com/inward/record.url?scp=78149418953&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=78149418953&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:78149418953
SN - 9781563479373
T3 - 46th AIAA Aerospace Sciences Meeting and Exhibit
BT - 46th AIAA Aerospace Sciences Meeting and Exhibit
PB - American Institute of Aeronautics and Astronautics Inc.
ER -