Investigation of flame flashback phenomenon in a supersonic crossflow with ethylene injection upstream of cavity flameholder

Zhao, Guoyan; Sun, Mingbo; Wu, Jinshui; Cui, Xingda; Wang, Hongbo

doi:10.1016/j.ast.2019.02.018

Cited by 62 publications

(8 citation statements)

References 49 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The Van-Driest transformed velocity versus dimensionless scale y+ based on three grid resolution levels has been depicted in Figure 6, where the theoretical solutions are also attached. Similar verification work has been done in reference 30. It can be seen that the coarse grid without additional refinements near the wall brings out maximum deviation, while the other two grids almost come to convergence.…”

Section: Experimental Description and Numerical Treatmentsupporting

confidence: 72%

“…So far, however, no clear understanding of the mechanisms inside the flame propagation and flame flashback phenomena has been recognized, requiring further detailed investigations. In the previous experimental researches, [28][29][30] an ethylene-fueled combustor was tested in our direct connect facilities with a total temperature of 1486K and inlet velocity of Mach 2.52, simulating the Mach 5.5 flight at a height of 25 km. The experimental analysis combined with the theoretical model has been adopted to explore the mechanism of flame flashback.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Tang

Zhao

Wang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

In this paper, the cavity parameters of length-to-depth ratio, aft ramp angle, and nitrogen throttling positions are numerically studied by a Large Eddy Simulation (LES) combined with the Flamelet/Progress Variable (FPV) model, to investigate the inducing factors and formation mechanism of flame flashback. These numerical studies are validated and compared to our previous experiments. It can be observed from both the calculated and experimental flow field that the larger length-to-depth ratio, sharper aft ramp angle, and nitrogen throttling closer to the cavity strengthen the mixing of fuel wake and promote the jet penetration depth. Meanwhile, the separation of the boundary layer downstream of the cavity can be induced by the shear layer, acoustic oscillation, as well as nitrogen throttling. And the above favorable prerequisites enhance the heat release nearby, while the reverse pressure gradient causes the enlargement of the boundary layer separation in turn. Under this positive feedback, thermal choking is formed and drives the reverse propagation of the high-temperature flame. It is concluded that the downstream boundary layer separation induced by the changes of the cavity parameters is a prerequisite for the flame flashback, and the formation of the thermal choking is the main reason for the flame flashback.

show abstract

Section: Experimental Description and Numerical Treatmentsupporting

confidence: 72%

Section: Introductionmentioning

confidence: 99%

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Tang

Zhao

Wang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

show abstract

“…The effect of a rough element on the hypersonic boundary layer receptivity was studied in Shi, Xu, Wang and Lv (2019). A flame flashback phenomenon in a supersonic crossflow with ethylene injection upstream of cavity flameholder was investigated in Zhao et al (2019). Effects of dimensional wall temperature on velocity-temperature correlations in supersonic turbulent channel flow of thermally perfect gas were studied in Chen, Li and Zhu (2019c).…”

Section: Applicationsmentioning

confidence: 99%

Essentially non-oscillatory and weighted essentially non-oscillatory schemes

Shu¹

2020

Acta Numerica

132

View full text Add to dashboard Cite

Essentially non-oscillatory (ENO) and weighted ENO (WENO) schemes were designed for solving hyperbolic and convection–diffusion equations with possibly discontinuous solutions or solutions with sharp gradient regions. The main idea of ENO and WENO schemes is actually an approximation procedure, aimed at achieving arbitrarily high-order accuracy in smooth regions and resolving shocks or other discontinuities sharply and in an essentially non-oscillatory fashion. Both finite volume and finite difference schemes have been designed using the ENO or WENO procedure, and these schemes are very popular in applications, most noticeably in computational fluid dynamics but also in other areas of computational physics and engineering. Since the main idea of the ENO and WENO schemes is an approximation procedure not directly related to partial differential equations (PDEs), ENO and WENO schemes also have non-PDE applications. In this paper we will survey the basic ideas behind ENO and WENO schemes, discuss their properties, and present examples of their applications to different types of PDEs as well as to non-PDE problems.

show abstract

“…The flame flashback phenomenon in an ethylene-fueled scramjet combustor was discovered and studied experimentally by Sun et al (2008Sun et al ( , 2012, Wang HB et al (2013), Wang ZG et al (2015), and Zhao et al (2019). The fuel was ignited by spark and formed an initial flame, which spread along the cavity shear layer and expanded to the main flow.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen

Wen

Tian

Zhang

et al. 2020

J. Zhejiang Univ. Sci. A

View full text Add to dashboard Cite

Flame stabilization in a kerosene-fueled scramjet combustor was investigated experimentally through Schlieren, flame luminosity, and wall pressure measurement, aiming to obtain better insight into combustion characteristics. Experiments were conducted in a direct-connected supersonic combustion facility with inflow conditions of Mach number 2.0, stagnation pressure 0.82 MPa, and temperature 950 K, simulating the flight condition of Mach number 4.0. Results revealed that kerosene was able to be ignited when the equivalence ratio of pilot hydrogen reached 0.080, but was unsuccessful when the equivalence ratio was 0.040. Once ignited, the intense combustion induced high back pressure forcing the flame to spread into the isolator. The pilot flame invariably appeared in the cavity shear layer and attached to the cavity ramp under different equivalence ratios of pilot hydrogen. With the mass flux of pilot hydrogen increased, the kerosene flame located near the cavity ramp was asymmetrical and unstable since it propagated upstream repeatedly. Therefore, the kerosene could be ignited by a suitable equivalence ratio of continuous pilot hydrogen, potentially accompanied with unstable combustion.

show abstract

Investigation of flame flashback phenomenon in a supersonic crossflow with ethylene injection upstream of cavity flameholder

Cited by 62 publications

References 49 publications

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Effects of cavity parameters on flame flashback phenomenon in a supersonic crossflow with a cavity flameholder

Essentially non-oscillatory and weighted essentially non-oscillatory schemes

Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen

Contact Info

Product

Resources

About