Investigations on flame liftoff characteristics in liquid-kerosene fueled supersonic combustor equipped with thin strut

Zhang, Junlong; Chang, Juntao; Jun-hai, MA; Wang, Youyin; Bao, Wen

doi:10.1016/j.ast.2018.11.017

Cited by 63 publications

(10 citation statements)

References 32 publications

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“…With a multistrut injector, due to the shock waves, the flow around the injector becomes subsonic and forms a recirculation region on both sides of the injector. [59][60][61][62] Besides, lambda shockwaves are seen, which further decelerates the airflow downstream of the strut. Separation regions are observed near the combustor's top and bottom walls owing to shock layer interactions.…”

Section: Resultsmentioning

confidence: 99%

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

2021

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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.

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Section: Resultsmentioning

confidence: 99%

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

2021

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“…An air-breathing hypersonic flight vehicle refers to an aircraft that has a flight Mach number of at least five. It is powered by an air-breathing scramjet engine [1][2][3][4]. However, the high Mach number of scramjet engines causes a severe problem with regard to thermal protection.…”

Section: Introductionmentioning

confidence: 99%

Study on influence of forced vibration of cooling channel on flow and heat transfer of hydrocarbon fuel at supercritical pressure

Chen

Han

et al. 2022

Therm sci

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The cooling channel of a scramjet is the fundamental structure of the active thermal protection for an engine. Till now, studies have focused mainly on the steady-state flow and heat transfer process in the cooling channel. However, the vibration intensity of an engine increases sharply as the flight speed increases, because of which, the flow and heat exchange mechanisms based on the cooling channel under stable conditions cannot be applied under vibration. In this study, experimental methods are used to study the characteristics of the forced vibration of a cooling channel on the flow and heat transfer of hydrocarbon fuel at supercritical pressure. In addition, the influences of different vibration frequencies and vibration amplitudes on the flow and heat transfer are analyzed. The research results show that at supercritical pressure, when the fuel temperature is below the critical temperature and the inner wall temperature is above the critical temperature, external vibrations would enhance the heat transfer characteristics of the cooling channel. However, when the pressure and temperature are unstable, the forced vibration of the cooling channel would suppress the instability of temperature and pressure while strengthening the heat exchange.

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“…The inclined injection upstream of the cavity reports lower total pressure losses compared to 90 degrees injection and consists of the flame inside of the cavity [25,26]. The mixing of the fuel-air and the efficiency of the combustion is affected by certain factors in case of the injection upstream of the cavity like fuel jet parameters, fuel jet-cavity interaction, and penetration extent of fuel jet [27][28][29]. Jeong et al [30] performed three hydrogen injection strategies in a cavity-based scramjet combustor.…”

Section: Introductionmentioning

confidence: 99%

The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor

2021

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This paper presents the effect of cavity-based injection in an axisymmetric supersonic combustor using numerical investigation. An axisymmetric cavity-based angled and transverse injections in a circular scramjet combustor are studied. A three-dimensional Reynolds-averaged Navier–Stokes (RANS) equation along with the k-ω shear-stress transport (SST) turbulence model and species transport equations are considered for the reacting flow studies. The numerical results of the non-reacting flow studies are validated with the available experimental data and are in good agreement with it. The performance of the injection system is analyzed based on the parameters like wall pressures, combustion efficiency, and total pressure loss of the scramjet combustor. The transverse injection upstream of the cavity and at the bottom wall of the cavity in a supersonic flow field creates a strong shock train in the cavity region that enhances complete combustion of hydrogen-air in the cavity region compared to the cavity fore wall injection schemes. Eventually, the shock train in the flow field enhances the total pressure loss across the combustor. However, a marginal variation in the total pressure loss is observed between the injection schemes.

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Investigations on flame liftoff characteristics in liquid-kerosene fueled supersonic combustor equipped with thin strut

Cited by 63 publications

References 32 publications

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

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

Study on influence of forced vibration of cooling channel on flow and heat transfer of hydrocarbon fuel at supercritical pressure

The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor

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