Investigation on the flameholding mechanisms in supersonic flows: backward-facing step and cavity flameholder

Huang, Wei; Pourkashanian, Mohamed; Ma, Lin; Ingham, D.B.; Luo, Shi; Wang, Zhen Guo

doi:10.1007/s12650-010-0064-8

Cited by 77 publications

(26 citation statements)

References 24 publications

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“…The backward-facing step can generate recirculation zones with low flow velocity and prolong the residence time of the flow formed in the step corner as discussed by Halupovich et al [8], Takahashi et al [9], and Mitani and Kouchi [10]. Recently, Huang et al [11] have investigated the flameholding mechanism in the combustor. They found that the vortices formed in the corner region of the backwardfacing step and in the cavity make a large difference to the enhancement of the mixing between the fuel and the free airstream and improve the mixing and combustion efficiency in the supersonic flow.…”

Section: Introductionmentioning

confidence: 99%

“…Most of numerical investigations for the backward-facing step in supersonic flow are based on either RANS or LES [10,11,18,[24][25][26]. RANS can give the averaged parameters of the flow field and predict the large-scale fluctuations through modeling, while LES is supposed to be more accurate theoretically, provided that only the subgrid scale eddy should be modeled according to the basic hypothesis of LES that the sub-grid scale is isotropic, and the larger eddies are calculated using Navier-Stokes equations.…”

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confidence: 99%

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Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Liu

Wang

Guo

et al. 2013

Advances in Mechanical Engineering

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The backward-facing step is practically implicated in many devices, encountering the massive separation flows. In the present study, simulations of supersonic flow over a backward-facing step have been carried out employing both RANS and LES. The simulated results are validated against the experimental data. The results of RANS and LES show a good comparison with the experimental results. Different inflow Mach numbers and expansion ratios are also investigated. The reattachment length decreases with the increase of inflow Mach number. The duct height has a great effect on the flow patterns. The present conclusions are helpful to understand the physics in supersonic separation flows and also provide theory basis for engineering applications.

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Section: Introductionmentioning

confidence: 99%

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confidence: 99%

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Liu

Wang

Guo

et al. 2013

Advances in Mechanical Engineering

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“…The numerical approach mentioned above has been utilized successfully to analyze the flow field in cases with a cavity (Huang et al, 2011a) and with transverse injection ports (Huang, 2014). For convenience, the code validation process is not provided in this section, and readers are referred to Huang et al (2011a) and Huang (2014).…”

Section: Code Validation and Grid Independency Analysismentioning

confidence: 99%

“…For convenience, the code validation process is not provided in this section, and readers are referred to Huang et al (2011a) and Huang (2014). A comparison between numerical results and published experimental data, as well as the grid independency analysis, has been provided by Huang et al (2011a) and Huang (2014). Fig.…”

Section: Code Validation and Grid Independency Analysismentioning

confidence: 99%

Supersonic mixing augmentation mechanism induced by a wall-mounted cavity configuration

Huang

Ding

et al. 2016

JZUS-A

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Abstract:An efficient mixing process is very important for the engineering implementation of an airbreathing propulsion system. The air and injectant should be mixed sufficiently before entering the combustor. Two new wall-mounted cavity configurations were proposed to enhance the mixing process in a conventional transverse injection flow field. Their flow field properties were compared with those of a system with only transverse injection ports. Grid independency analysis was used to choose a suitable grid scale, and the mixing efficiencies at four cross-sectional planes (namely x=20, 40, 60, and 80 mm, which are just downstream of the jet orifice) were compared for the configurations considered in this study. The results showed that hydrogen penetrated deeper when a cavity was mounted upstream of the transverse injection ports. This is beneficial to the mixing process in supersonic flows. The mixing efficiency of the configuration with the wall-mounted cavity was better than that of the conventional physical model, and the mixing efficiency of the proposed novel physical model I (98.71% at x=20 mm) was the highest of all. In the case with only transverse injection ports, the vortex was broken up by the strong interaction between the shear layer over the cavity and the jet.

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“…Therefore, the waverider is a good candidate for hypersonic flight [4]- [10]. Nowadays, there have been some remarkable vehicles which are designed based on waverider configuration, such as X-51A [11] and HTV-2.…”

Section: Introductionmentioning

confidence: 99%

Research on the drag reduction performance induced by the counterflowing jet for waverider with variable blunt radii

Wang

Barakos

et al. 2016

Acta Astronautica

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Waverider will endure the huge aero-heating in the hypersonic flow, thus, it need be blunt for the leading edge. However, the aerodynamic performance will decrease for the blunt waverider because of the drag hoik. How to improve the aerodynamic performance and reduce the drag and aero-heating is very important. The variable blunt radii method will improve the aerodynamic performance, however, the huge aero-heating and bow shock wave at the head is still serious. In the current study, opposing jet is used in the waverider with variable blunt radii to improve its performance. The three-dimensional coupled implicit Reynolds-averaged Navier-Stokes(RANS) equation and the two equation SST k-ω turbulence model have been utilized to obtain the flow field properties. The numerical method has been validated against the available experimental data in the open literature. The obtained results show that the L/D will drop 7~8% when R changes from 2 to 8. The lift coefficient will increase, and the drag coefficient almost keeps the same when the variable blunt radii method is adopted, and the L/D will increase. The variable blunt radii method is very useful to improve the whole characteristics of blunt waverider and the L/D can improve 3%. The combination of the variable blunt radii method and opposing jet is a novel way to improve the whole performance of blunt waverider, and L/D can improve 4~5%. The aperture as a novel way of opposing jet is suitable for blunt waverider and also useful to improve the aerodynamic and aerothermodynamic characteristics of waverider in the hypersonic flow. There is * Associate Professor, Corresponding author, E-mail address: gladrain2001@163.com, Phone: +86 731 84576447 -2 -the optimal P 0in /P 0 that can make the detached shock wave reattach the lower surface again so that the blunt waverider can get the better aerodynamic performance.

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Investigation on the flameholding mechanisms in supersonic flows: backward-facing step and cavity flameholder

Cited by 77 publications

References 24 publications

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Supersonic mixing augmentation mechanism induced by a wall-mounted cavity configuration

Research on the drag reduction performance induced by the counterflowing jet for waverider with variable blunt radii

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