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Experimental and numerical investigations on propagating modes of detonations: detonation wave/boundary layer interaction

Experimental and numerical investigations on propagating modes of detonations: detonation wave/boundary layer interaction
Experimental and numerical investigations on propagating modes of detonations: detonation wave/boundary layer interaction
In the present work the propagating modes of detonation wave in supersonic hydrogen-air mixtures are investigated in narrow rectangular channels. To clarify the effect of the detonation wave interaction with the boundary layer on the evolution and propagation of detonation phenomenon, high-speed laser schlieren experiments and adaptive Navier-Stokes (NS) simulations (pseudo-DNS) combined with a detailed reaction model are performed. The experimental results show that after successful ignition, two propagating modes are observed and can be classified as Oblique shock-induced combustion/Mach stem-induced detonation (OSIC/MSID) and pure Oblique shock-induced combustion (OSIC). For the OSIC/MSID mode, a Mach stem induced overdriven detonation is generated in the middle of the main flow. For the pure OSIC mode, no detonation wave but two oblique shock-induced combustion regions are generated throughout the whole channel with the overall structure taking a thwartwise V shape. The OSIC/MSID and pure OSIC propagation modes are further confirmed by pseudo-DNS employing a detailed reaction model and dynamic adaptive mesh refinement for the same conditions as utilized in the experiments. The numerical results show that because of subsonic combustion near the walls induced by the boundary layers, the OSIC/ MSID is not entirely symmetrical, while for the pure OSIC mode, larger fluctuations are observed along the oblique shock waves resulting from enhanced instabilities due to additional chemical heat release.
Supersonic combustible mixture; Detonation wave/boundary layer interaction; Propagation modes; Hot jet initiation
0010-2180
201-215
Cai, Xaidong
8d778bd0-f391-488d-b998-4f851382d9f8
Liang, Jianhan
fd8229b7-c7f4-4a1b-b94f-abce393f9e9a
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Mahmoudi, Yasser
5c336547-605b-4f01-afea-2fc24a922798
Sun, Mingbo
2df9eb75-e5d8-48cf-b8e1-00b0b77b3a90
Cai, Xaidong
8d778bd0-f391-488d-b998-4f851382d9f8
Liang, Jianhan
fd8229b7-c7f4-4a1b-b94f-abce393f9e9a
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Mahmoudi, Yasser
5c336547-605b-4f01-afea-2fc24a922798
Sun, Mingbo
2df9eb75-e5d8-48cf-b8e1-00b0b77b3a90

Cai, Xaidong, Liang, Jianhan, Deiterding, Ralf, Mahmoudi, Yasser and Sun, Mingbo (2018) Experimental and numerical investigations on propagating modes of detonations: detonation wave/boundary layer interaction Combustion and Flame, 190, pp. 201-215. (doi:10.1016/j.combustflame.2017.11.015).

Record type: Article

Abstract

In the present work the propagating modes of detonation wave in supersonic hydrogen-air mixtures are investigated in narrow rectangular channels. To clarify the effect of the detonation wave interaction with the boundary layer on the evolution and propagation of detonation phenomenon, high-speed laser schlieren experiments and adaptive Navier-Stokes (NS) simulations (pseudo-DNS) combined with a detailed reaction model are performed. The experimental results show that after successful ignition, two propagating modes are observed and can be classified as Oblique shock-induced combustion/Mach stem-induced detonation (OSIC/MSID) and pure Oblique shock-induced combustion (OSIC). For the OSIC/MSID mode, a Mach stem induced overdriven detonation is generated in the middle of the main flow. For the pure OSIC mode, no detonation wave but two oblique shock-induced combustion regions are generated throughout the whole channel with the overall structure taking a thwartwise V shape. The OSIC/MSID and pure OSIC propagation modes are further confirmed by pseudo-DNS employing a detailed reaction model and dynamic adaptive mesh refinement for the same conditions as utilized in the experiments. The numerical results show that because of subsonic combustion near the walls induced by the boundary layers, the OSIC/ MSID is not entirely symmetrical, while for the pure OSIC mode, larger fluctuations are observed along the oblique shock waves resulting from enhanced instabilities due to additional chemical heat release.

Text Experimental and Numerical Investigations on Propagating Modes - final - Accepted Manuscript
Restricted to Repository staff only until 22 December 2018.
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Accepted/In Press date: 15 November 2017
e-pub ahead of print date: 22 December 2017
Published date: April 2018
Keywords: Supersonic combustible mixture; Detonation wave/boundary layer interaction; Propagation modes; Hot jet initiation

Identifiers

Local EPrints ID: 416106
URI: https://eprints.soton.ac.uk/id/eprint/416106
ISSN: 0010-2180
PURE UUID: 45676698-3fa0-4695-9103-2c79fdd05114
ORCID for Ralf Deiterding: ORCID iD orcid.org/0000-0003-4776-8183

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Date deposited: 04 Dec 2017 17:30
Last modified: 03 Jan 2018 17:31

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Contributors

Author: Xaidong Cai
Author: Jianhan Liang
Author: Ralf Deiterding ORCID iD
Author: Yasser Mahmoudi
Author: Mingbo Sun

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