Small Business Innovation Research/Small Business Tech Transfer
Advanced Unsteady Turbulent Combustion Simulation Capability for Space Propulsion Systems, Phase I
Project Description
The innovation proposed here is a high performance, high fidelity simulation capability to enable accurate, fast and robust simulation of unsteady turbulent, reacting flows involving cryogenic propellants (such as LOX/LH2 and LOX/LCH4). The key features of this proposed capability are: (a) Hybrid RANS-LES (HRLES) methodology, and (b) flamelet modeling for turbulent combustion incorporated in a proven existing solver called Loci-STREAM which has been developed by the proposing personnel under funding from NASA over the last several years. The proposed enhancement in Loci-STREAM is anticipated to yield an order of magnitude improvement in simulation turnaround times relative to existing capability for turbulent reacting flow applications. The work proposed here will ultimately result in a state-of-the-art design and analysis tool to enable the accurate modeling of for multiphase combustion in solid and liquid rocket engines, combustion stability analysis, etc. which constitute critical components of versatile space propulsion engines part of NASA's deep space missions.
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Anticipated Benefits
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 combustion modeling capability, the applicability of this tool can be further broadened. The outcome of Phase I and Phase II research activities will be a powerful CFD-based design and analysis tool for propulsion engines at NASA. This tool is envisioned to very beneficial for space propulsion devices including full rocket engine simulations, injector design, etc. Specific applications at NASA of this capability include: (a) design improvements of J-2X and RS-68 injectors, (b) design of space propulsion engines involving LOX and LCH4 propellants, (c) modeling of multi-element injectors coupled with fuel and oxidizer feedlines and manifolds, (d) prediction of stability and stability margins, (e) design of acoustic cavities for combustion stability, etc.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
| Streamline Numerics, Inc. | Lead Organization | Industry | Gainesville, Florida |
Marshall Space Flight Center
(MSFC)
|
Supporting Organization | NASA Center | Huntsville, Alabama |
| University of Michigan-Ann Arbor | Supporting Organization | Academia | Ann Arbor, Michigan |
Primary U.S. Work Locations
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Alabama
-
Florida
-
Michigan
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This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.