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A Simple Approach for Thermal Analysis of Regenerative Cooling of Rocket Engines

[+] Author Affiliations
Mohammad H. Naraghi

Manhattan College, Riverdale, NY

Matthieu Foulon

École Catholique d’Arts et Métiers, Lyon, France

Paper No. IMECE2008-67988, pp. 531-538; 8 pages
doi:10.1115/IMECE2008-67988
From:
  • ASME 2008 International Mechanical Engineering Congress and Exposition
  • Volume 10: Heat Transfer, Fluid Flows, and Thermal Systems, Parts A, B, and C
  • Boston, Massachusetts, USA, October 31–November 6, 2008
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4871-5 | eISBN: 978-0-7918-3840-2
  • Copyright © 2008 by ASME

abstract

A simple model for thermal analysis of regenerative cooled rocket engines is developed. In this model the multi-dimensional heat conduction in the engine wall is analyzed using the fin effect of cooling channel side walls. A one-dimensional model for the cooling channel flow and heat transfer is used. The coolant properties are evaluated based on the NIST database. The present model is used to perform thermal analysis on two engines: the Space Shuttle Main Engine (a liquid hydrogen cooled engine) and a liquid oxygen cooled engine. Given the simplicity of the present approach its results compare well with other comprehensive models.

Copyright © 2008 by ASME

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