年間 6 号発行
ISSN 印刷: 2150-766X
ISSN オンライン: 2150-7678
Indexed in
REAL GAS EFFECTS SIMULATION IN A MODEL GH2/O2 ROCKET THRUST CHAMBER
要約
A CFD-model for a multicomponent reacting mixture of real gases at supercritical conditions is integrated into the KIVA-II code to analyze high pressure GH2/O2 ignition processes in a model single injector rocket thrust chamber. The model incorporates mixture thermodynamic anomalies accounted for in terms of the Redlich-Kwong equation for O2, while another species are treated as ideal, perfect gases, the k − ε turbulent submodel for compressible media, and equilibrium and finite-rate combustion chemistry. The detailed mechanism of H2/O2 oxidation is used to simulate ignition initiated by "hot spots". The "dense" gas formulation, in contrast to the ideal gas model, predicts mixing enhancement within the cylindrical part of the thrust chamber leading to a decrease in the oxygen jet core length, more stringent requirements for mixture flammability and reduced combustion efficiency. Using equilibrium chemistry, the model does not predict ignition and pressure rise time histories comparable to the results of calculation with finite-rate kinetics.