Faculty Mentor Name
Elliot Bryner
Format Preference
Poster
Abstract
During the shutdown or purge period after firing of a rocket engine it is critical to understand what equivalence ratios are desirable and implement a shutdown sequence so that the hardware is subjected to the lowest thermal and mechanical loading. Furthermore, it is essential that hazards to the test technicians caused by this method be minimized. The initial study was conducted into combustion mechanics, to understand how the reactants would ideally behave at varying equivalence ratios and in both pre-mixed and diffusion flame combustion. Using this foundation an analytical model for a Propane-Oxygen flame was created and tested using a scale combustion chamber and a pre-mixed gaseous flame. Finally, the pressure and exhaust gas temperature data will be used to create a solution to be implemented for further full-scale testing on a Kerosine-LOX liquid rocket engine.
Included in
Effects of Equivalence Ratio During Shutdown of a Rocket Engine on Hardware Longevity
During the shutdown or purge period after firing of a rocket engine it is critical to understand what equivalence ratios are desirable and implement a shutdown sequence so that the hardware is subjected to the lowest thermal and mechanical loading. Furthermore, it is essential that hazards to the test technicians caused by this method be minimized. The initial study was conducted into combustion mechanics, to understand how the reactants would ideally behave at varying equivalence ratios and in both pre-mixed and diffusion flame combustion. Using this foundation an analytical model for a Propane-Oxygen flame was created and tested using a scale combustion chamber and a pre-mixed gaseous flame. Finally, the pressure and exhaust gas temperature data will be used to create a solution to be implemented for further full-scale testing on a Kerosine-LOX liquid rocket engine.