Efficient multiphase rocket propellant injection model with high quality equation of state

Abstract

This paper reports on a new kind of real gas model, particularly suited for rocket injection applications. It di ffers from state-of-the-art models in two main ways: First, we use a precomputed library to store fluid data, instead of equation of state evaluation during runtime. Second, a newly developed multi-fluid-mixing model solves an individual equation of state (EOS) for each species, instead of evaluating a single EOS for a virtual pure fluid using van der Waals mixing or the corresponding states principle. This comes with a number of advantages: EOS evaluation becomes numerically very efficient; high delity EOS, such as Modifed Benedict-Webb-Rubin, may be used without performance penalty; the model allows for multiphase flow and phase change. The new model is demonstrated for several applications. Phase change is shown in 0D isobaric vaporization of oxygen, 1D combustion in an ideal gas limit. Finally, the model is applied to compute the reactive A60 Mascotte test case, where LOX and GH2 are coaxially injected at supercritical pressure. Maximum OH* concentration location is successfully predicted in the thin shear layer surrounding the LOX core.