期刊
PROCEEDINGS OF THE COMBUSTION INSTITUTE
卷 38, 期 3, 页码 3513-3520出版社
ELSEVIER SCIENCE INC
DOI: 10.1016/j.proci.2020.09.014
关键词
Detonation wave; Hypersonic premixed flow; Supersonic combustion; Deflagration to detonation transition; Shock-focusing
资金
- Air Force Office of Scientific Research [FA9550-16-10403, FA9550-19-1-0322]
- NASA Florida Space Grant Consortium through the Dissertation Improvement Fellowship
- Florida Education Fund through the McKnight Doctoral Fellowship
- TEES Eminent Research Professorship at Texas AM University
This research presents experimental evidence of controlled detonation initiation and propagation in a hypersonic flow of premixed hydrogen-air, defining three distinct flow regimes through flow diagnostics and simulation studies.
Experimental evidence of controlled detonation initiation and propagation in a hypersonic flow of premixed hydrogen-air is presented. This controlled detonation initiation is created in a hypersonic facility capable of producing a Mach 5 flow of hydrogen-air. Flow diagnostics such as high-speed schlieren and OH * chemiluminescence results show that a flame deflagration-to-detonation transition occurs as a combined result of turbulent flame acceleration and shock-focusing. The experimental results define three new distinct regimes in a Mach 5 premixed flow: deflagration-to-detonation transition (DDT), unsteady compressible turbulent flames, and shock-induced combustion. A two-dimensional implicit-LES (ILES) simulation, which solves the compressible, reactive Navier-Stokes equations on an adapting grid is conducted to provide additional insight into the local physical mechanism of detonation transition and propagation. (c) 2020 The Combustion Institute. Published by Elsevier Inc. All rights reserved.
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