Mechanism of detonation stabilization in a supersonic model combustor
Mechanism of detonation stabilization in a supersonic model combustor
The present work studies numerically the quasi-steady propagation of a hydrogen/oxygen detonation in a supersonic model combustor consisting of a cavity and an expanding wall. The two-dimensional reactive compressible Navier-Stokes equations with a one-step and two-species reaction model are solved using a hybrid sixth-order weighted essentially non-oscillatory-centred difference scheme combined with a structured adaptive mesh refinement technique. The results show that, after the shutdown of the hot jet, the detonation wave is successfully stabilized quasi-steadily in the supersonic model combustor together with periodic fluctuations of the detonation front. The formation of the quasi-steady propagation of detonation in the model combustor is mainly due to the combined effects of (i) pressure oscillations generated in the cavity, which facilitate the detonation propagation, and (ii) lateral mass divergence brought by the expanding wall, which can lead to detonation attenuation, and an unburned jet associated with large-scale vortices resulting from a Prandtl-Meyer expansion fan. This expansion fan is generated because of the expanding wall, which can contribute to the detonation stabilization. It is found that, for an incoming velocity lower than the Chapman-Jouguet value, a quasi-steady propagation of the detonation wave cannot be achieved. However, for incoming velocity higher than the Chapman-Jouguet value, a stabilization can be realized. This is effectively due to the formation of a periodic process, including four stages of forward propagation, detonation attenuation, backward propagation and detonation bifurcation, indicating the influence of the supersonic model combustor on the overall process.
Compressible Flows, Detonation waves, Detonations, Reacting Flows
Cai, Xiaodong
293bf621-f0e1-48ba-abaa-b41da81ea244
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Liang, Jianhan
fd8229b7-c7f4-4a1b-b94f-abce393f9e9a
Mahmoudi, Yasser
5c336547-605b-4f01-afea-2fc24a922798
Sun, Mingbo
2df9eb75-e5d8-48cf-b8e1-00b0b77b3a90
18 January 2021
Cai, Xiaodong
293bf621-f0e1-48ba-abaa-b41da81ea244
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Liang, Jianhan
fd8229b7-c7f4-4a1b-b94f-abce393f9e9a
Mahmoudi, Yasser
5c336547-605b-4f01-afea-2fc24a922798
Sun, Mingbo
2df9eb75-e5d8-48cf-b8e1-00b0b77b3a90
Cai, Xiaodong, Deiterding, Ralf, Liang, Jianhan, Mahmoudi, Yasser and Sun, Mingbo
(2021)
Mechanism of detonation stabilization in a supersonic model combustor.
Journal of Fluid Mechanics, 910, [A40].
(doi:10.1017/jfm.2020.920).
Abstract
The present work studies numerically the quasi-steady propagation of a hydrogen/oxygen detonation in a supersonic model combustor consisting of a cavity and an expanding wall. The two-dimensional reactive compressible Navier-Stokes equations with a one-step and two-species reaction model are solved using a hybrid sixth-order weighted essentially non-oscillatory-centred difference scheme combined with a structured adaptive mesh refinement technique. The results show that, after the shutdown of the hot jet, the detonation wave is successfully stabilized quasi-steadily in the supersonic model combustor together with periodic fluctuations of the detonation front. The formation of the quasi-steady propagation of detonation in the model combustor is mainly due to the combined effects of (i) pressure oscillations generated in the cavity, which facilitate the detonation propagation, and (ii) lateral mass divergence brought by the expanding wall, which can lead to detonation attenuation, and an unburned jet associated with large-scale vortices resulting from a Prandtl-Meyer expansion fan. This expansion fan is generated because of the expanding wall, which can contribute to the detonation stabilization. It is found that, for an incoming velocity lower than the Chapman-Jouguet value, a quasi-steady propagation of the detonation wave cannot be achieved. However, for incoming velocity higher than the Chapman-Jouguet value, a stabilization can be realized. This is effectively due to the formation of a periodic process, including four stages of forward propagation, detonation attenuation, backward propagation and detonation bifurcation, indicating the influence of the supersonic model combustor on the overall process.
Text
jfm-R2
- Accepted Manuscript
More information
Accepted/In Press date: 6 October 2020
Published date: 18 January 2021
Additional Information:
Funding Information:
This work is supported by the National Natural Science Foundation of China (no. 11702323), and the National Postdoctoral Program for Innovative Talent (no. BX20180372).
Publisher Copyright:
©
Keywords:
Compressible Flows, Detonation waves, Detonations, Reacting Flows
Identifiers
Local EPrints ID: 445013
URI: http://eprints.soton.ac.uk/id/eprint/445013
ISSN: 0022-1120
PURE UUID: 72358fb0-e87e-4dee-9f1a-8b315a58dc9f
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Date deposited: 18 Nov 2020 13:16
Last modified: 17 Mar 2024 05:58
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Contributors
Author:
Xiaodong Cai
Author:
Jianhan Liang
Author:
Yasser Mahmoudi
Author:
Mingbo Sun
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