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Validation of a Pressure-Based Combustion Simulation Tool Using a Single Element Injector Test ProblemThe traditional design and analysis practice for advanced propulsion systems, particularly chemical rocket engines, relies heavily on expensive full-scale prototype development and testing. Over the past decade, use of high-fidelity analysis and design tools such as CFD early in the product development cycle has been identified as one way to alleviate testing costs and to develop these devices better, faster and cheaper. Increased emphasis is being placed on developing and applying CFD models to simulate the flow field environments and performance of advanced propulsion systems. This necessitates the development of next generation computational tools which can be used effectively and reliably in a design environment by non-CFD specialists. A computational tool, called Loci-STREAM is being developed for this purpose. It is a pressure-based, Reynolds-averaged Navier-Stokes (RANS) solver for generalized unstructured grids, which is designed to handle all-speed flows (incompressible to hypersonic) and is particularly suitable for solving multi-species flow in fixed-frame combustion devices. Loci-STREAM integrates proven numerical methods for generalized grids and state-of-the-art physical models in a novel rule-based programming framework called Loci which allows: (a) seamless integration of multidisciplinary physics in a unified manner, and (b) automatic handling of massively parallel computing. The objective of the ongoing work is to develop a robust simulation capability for combustion problems in rocket engines. As an initial step towards validating this capability, a model problem is investigated in the present study which involves a gaseous oxygen/gaseous hydrogen (GO2/GH2) shear coaxial single element injector, for which experimental data are available. The sensitivity of the computed solutions to grid density, grid distribution, different turbulence models, and different near-wall treatments is investigated. A refined grid, which is clustered in the vicinity of the solid walls as well as the flame, is used to obtain a steady state solution which may be considered as the best solution attainable with the steady-state RANS methodology. From a design point of view, quick turnaround times are desirable; with this in mind, coarser grids are also employed and the resulting solutions are evaluated with respect to the fine grid solution.
Document ID
20060016364
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Thakur, Siddarth
(Streamline Numerics, Inc. Gainesville, FL, United States)
Wright, Jeffrey
(Streamline Numerics, Inc. Gainesville, FL, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2006
Subject Category
Propellants And Fuels
Meeting Information
Meeting: 3rd International Workshop on Rocet Combustion Modeling
Location: Paris
Country: France
Start Date: March 12, 2006
End Date: March 15, 2006
Funding Number(s)
CONTRACT_GRANT: NNM05AA87C
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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