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Fully Coupled Aero-Thermochemical-Elastic Simulations of an Eroding Graphite NozzleA multiphysics simulation capability has been developed that incorporates mutual interactions between aerodynamics, structural response from aero/thermal loading, ablation/pyrolysis, heating, and surface-to-surface radiation to perform high-fidelity, fully coupled aerothermoelastic ablation simulations, which to date had been unattainable. The multiphysics framework couples CHAR (a 3-D implicit charring ablator solver), Loci/CHEM (a computational fluid dynamics solver for high-speed chemically reacting flows), and Abaqus (a nonlinear structural dynamics solver) to create a fully coupled aerothermoelastic charring ablative solver. The solvers are tightly coupled in a fully integrated fashion to resolve the effects of the ablation pyrolysis and charring process and chemistry products upon the flow field, the changes in surface geometry due to recession upon the flow field, and thermal-structural analysis of the body from the induced aerodynamic heating from the flow field. The multiphysics framework was successfully demonstrated on a solid rocket motor graphite nozzle erosion application. Comparisons were made with available experimental data that measured the throat erosion during the motor firing. The erosion data is well characterized, as the test rig was equipped with a windowed nozzle section for real-time X-ray radiography diagnostics of the instantaneous throat variations for deducing the instantaneous erosion rates. The nozzle initially undergoes a nozzle contraction due to thermal expansion before ablation effects are able to widen the throat. A series of parameters studies were conducted using the coupled simulation capability to determine the sensitivity of the nozzle erosion to different parameters. The parameter studies included the shape of the nozzle throat (flat versus rounded), the material properties, the effect of the choice of turbulence model, and the inclusion or exclusion of the mechanical thermal expansion. Overall, the predicted results match the experiment very well, and the predictions were able to bound the data within acceptable limits.
Document ID
20170005288
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Blades, E. L.
(ATA Engineering, Inc. San Diego, CA, United States)
Reveles, N. D.
(ATA Engineering, Inc. San Diego, CA, United States)
Nucci, M.
(ATA Engineering, Inc. San Diego, CA, United States)
Maclean, M.
(CUBRC, Inc. Buffalo, NY, United States)
Date Acquired
June 7, 2017
Publication Date
May 22, 2017
Subject Category
Fluid Mechanics And Thermodynamics
Spacecraft Propulsion And Power
Report/Patent Number
M17-6059
Report Number: M17-6059
Meeting Information
Meeting: JANNAF Rocket Nozzle Technology Meeting
Location: Kansas City, MO
Country: United States
Start Date: May 22, 2017
End Date: May 25, 2017
Sponsors: Department of the Army, Department of the Navy, NASA Headquarters, Department of the Air Force
Funding Number(s)
CONTRACT_GRANT: NNX16CM45P
Distribution Limits
Public
Copyright
Public Use Permitted.
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