Parametric effects in a scramjet engine on the interaction between the air stream and the injection

Huang, Wei; Ma, Lin; Pourkashanian, Mohamed; Ingham, D.B.; Luo, S-B; Wang, Z-G

doi:10.1177/0954410011408512

Cited by 36 publications

(9 citation statements)

References 18 publications

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“…17 At the same time, the multi-port injection scheme is better than the single one in the aspect of fuel penetration when the distance between the injectors is short enough, namely m ¼ 1 mm in the current study, and this may be induced by the stronger shock wave/shock wave interaction between the injectors (see Table 3 and Figure 13 in Huang et al 15 ). However, the region for the mixing between the boundary layer and fuel jet upstream of the first injector is small.…”

Section: Resultsmentioning

confidence: 89%

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Huang

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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The staged injection scheme has drawn an increasing attention for the airbreathing hypersonic propulsion system, and the fuel injection angle has a large impact on the mixing improvement between the fuel and the supersonic cross flow. The Reynolds-averaged Navier-Stokes equations associated with the SST k-! turbulence model have been employed to investigate the interaction mechanism in the staged sonic injection flow field, and the influences of the injection angle, the injection angle arrangement, and the distance between the injectors on the flow field characteristics have been analyzed comprehensively. At the same time, three grid scales have been used to perform the grid independency analysis, and the predicted results have been compared with the experimental data in the open literature for the single transverse injection scheme. The obtained results show that the penetration height for the cases with the distance between the injectors being 1 mm is the highest in the range considered in the current study, and this may be due to the strongest shock wave/shock wave interaction between the injectors. At the same time, due to the blockage of the fuel injection, the penetration height increases as the supersonic air stream flows downstream, and the influence of the wave system generated by the first and third injectors cannot propagate downstream and upstream, respectively. The multi-port injection scheme can provide better fuel penetration performance than the single one when the flow flux keeps constant, and the multi-port injection scheme with a certain angle can provide a higher total pressure recovery efficiency than the staged transverse injection scheme. Further, the staged transverse injection flow field can provide a better recirculation zone for the mixing between the fuel jet and the boundary layer, and the separation length increases with the increase of the distance between the injectors.

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Section: Resultsmentioning

confidence: 89%

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Huang

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…To satisfy the requirements in engineering, researchers mainly focus on time-averaged penetration height, mass fraction distribution, total pressure loss in the following four aspects, namely jet-to-freestream momentum flux ratio [4,[14][15][16][17], injection angle [4,[18][19][20], configuration of injection orifice [4,21], molecular weight [21][22][23]. However, limited by experimental measurements and numerical simulations, the turbulent characteristics of sonic jet in supersonic crossflow are not the major contents in the early studies.…”

Section: Introductionmentioning

confidence: 98%

Investigation of injectant molecular weight effect on the transverse jet characteristics in supersonic crossflow

et al. 2015

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“…However, these devices are intrusive to the flow, generate drag, and require cooling [9]. Therefore, the flush-wall injection continues to remain one of the simplest and most promising strategies to enhance the mixing process between the air and injectant in supersonic flows, and it attracts an increasing attention since the early sixties [10][11][12][13][14][15][16][17]. Huang and Yan [18] provided a detailed review on the transverse injection flow field in supersonic flows, and its four aspects were summarized, namely the jet-to-crossflow pressure ratio, the geometric configuration of the injection port, the number of injection ports and the injection angle.…”

Section: Introductionmentioning

confidence: 99%

Mixing augmentation mechanism induced by the pseudo shock wave in transverse gaseous injection flow fields

Huang

Yan

2016

International Journal of Hydrogen Energy

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The mixing process between the injectant and air is very crucial for the engineering implementation of the scramjet engine, and this is due to the very short resident time of fuel in supersonic flows. In the current study, the three-dimensional Reynolds-average Navier-Stokes (RANS) equations coupled with the two equation k-ω shear stress transport (SST) turbulence model have been employed to investigate the transverse injection flow field with the pseudo shock wave induced by the high back pressure, and the freestream Mach number is 3.75. At the same time, the influence of the back pressure on the flow field properties has been evaluated as well. The obtained results show that the pseudo shock wave induced by the back pressure plays an important role in the mixing enhancement between the injectant and air. When the back pressure ratio is larger than 5.0, the mixing efficiency increases with the increase of the back pressure ratio. However, when the back pressure ratio is 3.0, the near-field mixing process has been improved, and accordingly its mixing efficiency in this region is larger than the benchmark. This implies that the intense combustion downstream of the injector can enhance the mixing process between the injectant and air, and the mixing and combustion process can be enhanced mutually. When the pseudo shock wave has been pushed upstream of the wall orifice, more injectant has been brought into the separation zone upstream of the injector, and this is beneficial for the mixing process between the

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Parametric effects in a scramjet engine on the interaction between the air stream and the injection

Cited by 36 publications

References 18 publications

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow

Investigation of injectant molecular weight effect on the transverse jet characteristics in supersonic crossflow

Mixing augmentation mechanism induced by the pseudo shock wave in transverse gaseous injection flow fields

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