An efficient multi-fluid-mixing model for real gas reacting flows in liquid propellant rocket engines

摘要: Abstract This paper introduces a new model for real gas thermodynamics, with improved accuracy, performance, and robustness compared to state-of-the-art models. It is motivated by the physical insight that in non-premixed flames, as encountered high pressure liquid propellant rocket engines, mixing takes place chiefly hot reaction zone among ideal gases. We developed taking advantage of this: When fluid behavior only occurs cryogenic oxygen stream, this where equation state (EOS) required. All other species thermodynamic can be treated ideal. Real properties are stored library; evaluation EOS moved preprocessing step. Thus decoupling from runtime method allows application accurate quality or tabulated data without penalty. provides fast robust iteration even near critical point multiphase coexistence region. The has been validated successfully applied computation 0D phase change heat addition, supercritical reactive coaxial LOX/GH 2 single injector.