Abstract
Using a detailed kinetic mechanism of the chemical interaction, detonation combustion of a stoichiometrical hydrogen-air mixture flowing at a supersonic velocity into a plane symmetrical channel with a constriction has been investigated with the purpose of both determination of conditions that provide detonation stabilization in the flow and study of methods of stabilized wave location control.
In case of detonation initiation by energy input, the investigation of conditions of formation in the channel of a thrust developing flow with a stabilized detonation wave was carried out. The effect of variations of the inflow Mach number, the dustiness of the incoming gas mixture, and the width of the outflow channel cross section on stabilized detonation location was examined. Some methods of controlling of detonation location in the flow that ensure a thrust increase have been proposed. The possibility of formation of the thrust developing flow with a stabilized detonation wave in the channel under consideration without any energy consumption has been detected.
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Acknowledgments
This research has been supported by the Russian Foundation for Basic Research (projects Nos. 16-29-01092 and 18-01-00883) and the Ministry of Education and Science of the Russian Federation (contract 14.G39.31.0001 from 13.02.2017). This research has been supported by the Supercomputing Center of Lomonosov Moscow State University [9].
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Levin, V., Zhuravskaya, T. (2019). Gas Flow with Stabilized Detonation in a Plane Channel. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 1. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91020-8_32
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DOI: https://doi.org/10.1007/978-3-319-91020-8_32
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