Please use this identifier to cite or link to this item:
https://hdl.handle.net/2440/57338
Type: | Thesis |
Title: | High pressure LOx/H₂ rocket engine combustion. |
Author: | Smith, Joshua John |
Issue Date: | 2007 |
School/Discipline: | School of Mechanical Engineering |
Abstract: | This thesis describes a study based on propellant injection conditions which was performed with a single shear coaxially injected liquid rocket engine combuster. Steady state operation was closely examined with the thrust chamber operating at sub critical, near critical and supercritical pressure levels with respect to the thermodynamic critical pressure of oxygen. It was found that unstable combustion could not be triggered whatsoever with LOx/H₂ propellants at near or supercritical pressure, irrespective of operating conditions. Such findings illustrate that operating near or above the critical pressure of propellants (oxygen) results in inherently stable combustion process over a broad range of operating conditions. |
Dissertation Note: | Thesis (Ph.D.) -- University of Adelaide, School of Mechanical Engineering, 2007 |
Keywords: | rockets (aeronautics) launching; combustion engineering |
Provenance: | This electronic version is made publicly available by the University of Adelaide in accordance with its open access policy for student theses. Copyright in this thesis remains with the author. This thesis may incorporate third party material which has been used by the author pursuant to Fair Dealing exception. If you are the author of this thesis and do not wish it to be made publicly available or If you are the owner of any included third party copyright material you wish to be removed from this electronic version, please complete the take down form located at: http://www.adelaide.edu.au/legals |
Appears in Collections: | Research Theses |
Files in This Item:
File | Description | Size | Format | |
---|---|---|---|---|
01front.pdf | 96.41 kB | Adobe PDF | View/Open | |
02whole.pdf | 13.37 MB | Adobe PDF | View/Open |
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.