Graduation Semester and Year
2018
Language
English
Document Type
Thesis
Degree Name
Master of Science in Aerospace Engineering
Department
Mechanical and Aerospace Engineering
First Advisor
Donald R Wilson
Abstract
The objective of this research is to simulate normal detonation combustion which is a mode of operation for a Pulsed Detonation Engine (PDE). A supersonic flow with stoichiometric hydrogen-air mixture is made to impinge on a wedge, thus resulting in increasing the temperature and pressure across a shock wave leading to the formation of detonation wave. Different modes of the operations can be simulated by varying the incoming Mach number, pressure, temperature and equivalence ratio. For the case of normal detonation wave mode which is an unsteady process, after the detonation being initiated due to the shock induced by the wedge, the detonation wave propagates upstream in the flow as the combustion chamber Mach number is lower than the C-J Mach number. The concept of detonation wave moving upstream and downstream is controlled by changing the incoming flow field properties. By this method the unsteady normal detonation wave is made to oscillate in the combustion chamber leading to a continuous detonation combustion. The intention of this research is to simulate two cycles of detonation combustion in order to determine the frequency and to obtain the variation of flow properties at the exit plain with respect to time.
Keywords
Detonation, Numerical simulation
Disciplines
Aerospace Engineering | Engineering | Mechanical Engineering
License
This work is licensed under a Creative Commons Attribution-NonCommercial-Share Alike 4.0 International License.
Recommended Citation
Omprakas, Ajjay, "Numerical simulation of unsteady normal detonation combustion" (2018). Mechanical and Aerospace Engineering Theses. 811.
https://mavmatrix.uta.edu/mechaerospace_theses/811
Comments
Degree granted by The University of Texas at Arlington