Detonation-based combustion systems are desired for propulsion and power systems due to their ability to provide high thermal efficiency and enable supersonic flight. Detonation combustion in hypersonic flows has traditionally been realized using an oblique detonation wave. However, oblique detonation realization and stabilization in combustion systems is challenging. This communication presents an alternative realization of a detonation mode of combustion through a reacting Mach stem. The detonation is experimentally realized in a hypersonic reacting facility, which is optimized for Mach 5 flow at the combustor inlet and includes a 2D-wedge to stabilize hypersonic reactions at high-enthalpy flow conditions. The Mach stem detonation is analyzed with simultaneous 30 kHz schlieren and chemiluminescence imaging, which reveals the coupling between the Mach stem and the reaction. Further confirmation is provided by comparing the Mach number of the reacting Mach stem with the Chapman-Jouguet (CJ) detonation Mach number. It is found that the Mach number of the reacting Mach stem reaches 94% of the CJ detonation Mach number, confirming that the reacting Mach stem realizes a detonation mode of combustion.
| Identifer | oai:union.ndltd.org:ucf.edu/oai:stars.library.ucf.edu:etd2023-1120 |
| Date | 01 January 2023 |
| Creators | Kotler, Adam R |
| Publisher | STARS |
| Source Sets | University of Central Florida |
| Language | English |
| Detected Language | English |
| Type | text |
| Format | application/pdf |
| Source | Graduate Thesis and Dissertation 2023-2024 |
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