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Computational Study on a Single Flow Element in a Nuclear Thermal Rocket

[+] Author Affiliations
Xiang Zhao, Trent Montgomery

Alabama A&M University, Huntsville, AL

Sijun Zhang

ESI CFD, Inc., Huntsville, AL

Paper No. ICONE21-15683, pp. V003T10A023; 11 pages
doi:10.1115/ICONE21-15683
From:
  • 2013 21st International Conference on Nuclear Engineering
  • Volume 3: Nuclear Safety and Security; Codes, Standards, Licensing and Regulatory Issues; Computational Fluid Dynamics and Coupled Codes
  • Chengdu, China, July 29–August 2, 2013
  • Conference Sponsors: Nuclear Engineering Division
  • ISBN: 978-0-7918-5580-5
  • Copyright © 2013 by ASME

abstract

The nuclear thermal rocket is one of the candidate propulsion systems for future space exploration including traveling to Mars and other planets of the solar system. Nuclear thermal propulsion can provide a much higher specific impulse than the best chemical propulsion available today. A basic nuclear propulsion system consists of one or several nuclear reactors that heat hydrogen propellant to high temperatures and then allow the heated hydrogen and its reacting product to flow through a nozzle to produce thrust. This paper presents computational study on a single flow element in a nuclear thermal rocket. The computational results provide both detailed and global thermo-fluid environments of a single flow element for thermal stress estimation and insight for possible occurrence of mid-section corrosion.

Copyright © 2013 by ASME

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