Date of Award
2011-01-01
Degree Name
Master of Science
Department
Mechanical Engineering
Advisor(s)
Jack Chessa
Abstract
Liquid rocket engines benefit in life cycle from the active regenerative cooling method which passes the fuel as the coolant through channels surrounding the combustion chamber. These channels are designed and optimized using structural considerations as well as heat transfer theory, then CFD simulations with the software FLUENT are performed for the final analysis. The difficulty in using methane as the fuel/coolant is addressed, and requires the use of the ideal gas numerical model in preliminary CFD simulations. Comparison to real gas numerical models is made, and results also given for one channel design. The techniques utilized herein allow the choice of the "optimal" cooling channel configuration for the cSETR 50lbf engine specifically, but the methods can be used for other configurations.
Language
en
Provenance
Received from ProQuest
Copyright Date
2011
File Size
214 pages
File Format
application/pdf
Rights Holder
Christopher Linn Bradford
Recommended Citation
Bradford, Christopher Linn, "Design and CFD Optimization of Methane Regenerative Cooled Rocket Nozzles" (2011). Open Access Theses & Dissertations. 2242.
https://scholarworks.utep.edu/open_etd/2242