Numerical investigation on mixing behavior of fuels inreacting and non-reacting flow condition of a cavity-strut based scramjet combustor

Suneetha, Lakka; Randive, Pitambar; Pandey, Krishna Murari

doi:10.1016/j.ijhydene.2019.04.262

Cited by 29 publications

(8 citation statements)

References 76 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The model transport equation called the Shear Stress Transport (SST) k-ω model [15,48,49] with default constants was used for solving the turbulent flow field. The SST k-ω turbulence model provides a good prediction of mixing layers and jet flows [18,19,29]. The flow is considered to be ideal gas, and the thermal conductivity and viscosity are computed using mass-weighted-mixing-law.…”

Section: Methodsmentioning

confidence: 99%

“…There are various injection and flame holding mechanisms, such as cavities [4][5][6][7][8][9][10], pylons [11][12][13][14] and struts [15][16][17][18][19][20][21][22][23][24][25][26][27][28]. The combinations of the aforementioned schemes [29][30][31][32] were succeeded to some extend by several studies. A strut-based injector configuration is among those that could solve the aforesaid issues and also uphold the minimum total pressure loss.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

et al. 2021

View full text Add to dashboard Cite

This paper focuses on the influence of ramp locations upstream of a strut-based scramjet combustor under reacting flow conditions that are numerically investigated. In contrast, a computational study is adopted using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport (SST) k-ω turbulence model. The numerical results of the Deutsches Zentrum für Luft- und Raumfahrt or German Aerospace Centre (DLR) scramjet model are validated with the reported experimental values that show compliance within the range, indicating that the adopted simulation method can be extended for other investigations as well. The performance of the ramps in the strut-based scramjet combustor is analyzed based on parameters such as wall pressures, combustion efficiency and total pressure loss at various axial locations of the combustor. From the numerical shadowgraph, more shock interactions are observed upstream of the strut injection region for the ramp cases, which decelerates the flow downstream, and additional shock reflections with less intensity are also noticed when compared with the DLR scramjet model. The shock reflection due to the ramps enhances the hydrogen distribution in the spatial direction. The ignition delay is noticed for ramp combustors due to the deceleration of flow compared to the baseline strut only scramjet combustor. However, a higher flame temperature is observed with the ramp combustor. Because more shock interactions arise from the ramps, a marginal increase in the total pressure loss is observed for ramp combustors when compared to the baseline model.

show abstract

Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

et al. 2021

View full text Add to dashboard Cite

show abstract

“…An efficient fuel injection system necessitates for complete combustion of hydrogen fuel in the scramjet combustor, which could enhance the mixing and combustion of fuel and air with minimum total pressure loss. Various injection and flame holding strategies such as flush wall injection (Goyne et al, 2001;Tahani et al, 2016), cavities (Assis et al, 2019;Jeyakumar et al, 2006Jeyakumar et al, , 2017Jeyakumar et al, , 2018Wang et al, 2020), pylons (Doster et al, 2007;Gruber et al, 2008;Lee, 2012) and struts (Bresson et al, 2001;Huang et al, 2017;Liu et al, 2019) and their combinations (Freeborn et al, 2009;Lakka et al, 2021;Montes et al, 2005;Suneetha et al, 2019aSuneetha et al, , 2019b were attempted and succeeded to some extend by many researchers. A strut-based injector configuration is among the ones that could solve the aforementioned issues and also limit the total pressure loss.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

Jeyakumar

Jayaraman

Sivakumar

et al. 2021

AEAT

View full text Add to dashboard Cite

Purpose This paper aims to study the influences of hydrogen jet pressure on flow features of a strut-based injector in a scramjet combustor under-reacting cases are numerically investigated in this study. Design/methodology/approach The numerical analysis is carried out using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport k-ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters such as the shock wave pattern, wall pressures and static temperature across the combustor are validated with the reported experiments. The results comply with the range, indicating the adopted simulation method can be extended for other investigations as well. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency and total pressure loss. Findings The results revealed that the augmentation of hydrogen jet pressure via variation in flame features increases the static pressure in the vicinity of the strut and destabilize the normal shock wave position. Indeed, the pressure of the mainstream flow drives the shock wave toward the upstream direction. The study perceived that once the hydrogen jet pressure is reached 4 bar, the incoming flow attains a subsonic state due to the movement of normal shock wave ahead of the strut. It is noticed that the increase in hydrogen jet pressure in the supersonic flow field improves the jet penetration rate in the lateral direction of the flow and also increases the total pressure loss as compared with the baseline injection pressure condition. Practical implications The outcome of this research provides the influence of fuel injection pressure variations in the supersonic combustion phenomenon of hypersonic vehicles. Originality/value This paper substantiates the effect of increasing hydrogen jet pressure in the reacting supersonic airstream on the performance of a scramjet combustor.

show abstract

“…7,8 An efficient fuel injection system necessitates complete combustion of the hydrogen in the scramjet combustor, enhancing the mixing along with combustion of fuel and oxidant with minimum total pressure loss. Various injection and flame holding strategies, like, flush wall injection, 9,10 cavities, [11][12][13][14][15] pylons, 4,16,17 struts, 5,18,19 and so forth, and their combinations [20][21][22][23][24] are attempted and succeeded to some extent by many researchers. A strut-based injector configuration is among the ones that could solve the issues mentioned above and also limit the total pressure loss.…”

Section: Introductionmentioning

confidence: 99%

“…The inclusion of multijet improves the mixing rate, an eight-inline injected jet increased the mixing rate by 45% near the injection port when compared with a single jet. Suneetha et al 23 numerically studied fuel mixing using hydrogen and ethylene as fuel in a reacting and nonreacting cavity-based scramjet combustor with triangular strut injection. It is observed that maximum efficiency of mixing is obtained at a Mach number of 2.5 for hydrogen and 3.5 for ethylene for considered geometry and inlet conditions.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

2021

View full text Add to dashboard Cite

This study aims at investigating the effect of a multistrut-based hydrogen injector in a scramjet combustor underreacting case. The numerical analysis is carried out using two-dimensional Reynolds-averaged Navier-Stokes equations with the Shear Stress Transport k − ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters, such as the shock wave pattern, wall pressures, and static temperature across the combustor, are validated with the reported experimental results. The results comply with the range, indicating that the adopted simulation method for single strut injection can be extended for other investigations. It is noticed that with multistrut injectors, as hydrogen jet pressure increases in the supersonic flow field, the jet penetration rate in the lateral direction of the flow and the total pressure loss as compared with the baseline injection pressure conditions has increased. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency, mixing efficiency, and total pressure loss. Compared with the single-strut output of a scramjet combustor, multistruts inclusion increased the combustion efficiency by almost 18%, the mixing efficiency attained the maximum with 16% fewer lengths. The total pressure loss in single-strut is 14% lower than that of multistrut.

show abstract

Numerical investigation on mixing behavior of fuels inreacting and non-reacting flow condition of a cavity-strut based scramjet combustor

Cited by 29 publications

References 76 publications

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

Contact Info

Product

Resources

About