The outcome of this work will be a powerful CFD-based design and analysis tool for propulsion engines of relevance to NASA. This tool is envisioned to be useful for full rocket engine simulations, injector design, etc. Specific applications at NASA of this capability include: (a) High-fidelity simulations of upper stage propulsion systems, (b) The multi-element injector problem coupled with fuel and oxidizer feedlines and manifolds, (c) Design improvements for J-2X and RS-68 injectors to be used in the SLS, (d) Design improvements for the LOX/LH2, LOX/LCH4 and LOX/RP-1 engines, and (e) full rocket engine simulations.
The computational tool resulting from this project will have wide-ranging commercial applications. The Hybrid RANS-LES methodology can be used for a wide variety of engineering applications involving unsteady turbulent flows. The reacting flow capability can be used for simulating combusting flows in various industrial applications, such as gas turbine engines, diesel engines, etc. The real-fluids methodology can be used in a large number of industrial flow situations involving both chemically inert and reacting flows. With additions of multi-phase spray combustion modeling capability, the applicability of this tool can be further broadened.