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CFD Code Validation of Wall Heat Fluxes for a G02/GH2 Single Element CombustorThis paper puts forth the case for the need for improved injector design tools to meet NASA s Vision for Space Exploration goals. Requirements for this improved tool are outlined and discussed. The potential for Computational Fluid Dynamics (CFD) to meet these requirements is noted along with its current shortcomings, especially relative to demonstrated solution accuracy. The concept of verification and validation is introduced as the primary process for building and quantifying the confidence necessary for CFD to be useful as an injector design tool. The verification and validation process is considered in the context of the Marshall Space Flight Center (MSFC) Combustion Devices CFD Simulation Capability Roadmap via the Simulation Readiness Level (SRL) concept. The portion of the validation process which demonstrates the ability of a CFD code to simulate heat fluxes to a rocket engine combustor wall is the focus of the current effort. The FDNS and Loci-CHEM codes are used to simulate a shear coaxial single element G02/GH2 injector experiment. The experiment was conducted a t a chamber pressure of 750 psia using hot propellants from preburners. A measured wall temperature profile is used as a boundary condition to facilitate the calculations. Converged solutions, obtained from both codes by using wall functions with the K-E turbulence model and integrating to the wall using Mentor s baseline turbulence model, are compared to the experimental data. The initial solutions from both codes revealed significant issues with the wall function implementation associated with the recirculation zone between the shear coaxial jet and the chamber wall. The FDNS solution with a corrected implementation shows marked improvement in overall character and level of comparison to the data. With the FDNS code, integrating to the wall with Mentor s baseline turbulence model actually produce a degraded solution when compared to the wall function solution with the K--E model. The Loci-CHEM solution, produced by integrating to the wall with Mentor s baseline turbulence model, matches both the heat flux rise rate in the near injector region and the peak heat flux level very well. However, it moderately over predicts the heat fluxes downstream of the reattachment point. The Loci-CHEM solution achieved by integrating to the wall with Mentor s baseline turbulence model was clearly superior to the other solutions produced in this effort.
Document ID
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Lin, Jeff
(NASA Marshall Space Flight Center Huntsville, AL, United States)
West, Jeff S.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Williams, Robert W.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Tucker, P. Kevin
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 8, 2013
Publication Date
January 1, 2005
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2005-4524
Meeting Information
Meeting: 41st AIAA/ASME/SAE Joint Propulsion Conference
Location: Tucson, AZ
Country: United States
Start Date: July 10, 2005
End Date: July 13, 2005
Sponsors: American Society of Mechanical Engineers, Society of Automotive Engineers, Inc., American Inst. of Aeronautics and Astronautics
Distribution Limits
Work of the US Gov. Public Use Permitted.
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