Experimental study on the effects of simulated flight conditions on ignition and flame stabilization in a supersonic combustor

Li, Lang; Qiao, Wenyou

doi:10.1016/j.ast.2019.05.050

Cited by 25 publications

(2 citation statements)

References 26 publications

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“…Zhong et al (2019) analyzed experimentally the flame characteristics of different fuels in the supersonic combustor and found that their ignition process is similar, but the frequency of the flame oscillations depends on the fuel type. Li and Qiao (2019) studied the effect of inlet conditions on the ignition and flame stabilization of the supersonic combustion chamber and showed that the air throttling may help to achieve the flame stabilization.…”

Section: Introductionmentioning

confidence: 99%

Inlet air and fuel flow pressure fluctuation effect on supersonic combustion

Tahsini

2020

AEAT

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Purpose The purpose of this paper is to analyze the effect of pressure fluctuations on the combustion efficiency of the hydrogen fuel injected into the supersonic oxidizing cross flow. The pressure fluctuations are imposed on inlet air flow and also on the fuel flow stream. Two different situations are considered: the combustion chamber once without and again with the inlet standing oblique shock wave. Design/methodology/approach The pressure fluctuations are imposed on inlet air flow and also on the fuel flow stream. Two different situations are considered: the combustion chamber once without and again with the inlet standing oblique shock wave. The unsteady turbulent reacting flow solver is developed to simulate the supersonic flow field in the combustion chamber with detail chemical kinetics, to predict the time-variation of the combustion efficiency due to the imposed pressure fluctuations. Findings The results show that the response of the reacting flow field depends on both the frequency of fluctuations and the existence of the inlet shock wave. In addition, the inlet standing shock wave has some attenuating role, but the reacting flow shows an amplifying role on imposed oscillations which is also augmented by imposing anti-phase fluctuations on both inlet and fuel flow streams. Originality/value This study is performed to analyze the instabilities in the supersonic combustion which has not been considered before in this manner.

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Section: Introductionmentioning

confidence: 99%

Inlet air and fuel flow pressure fluctuation effect on supersonic combustion

Tahsini

2020

AEAT

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“…9 analyzed experimentally the flame characteristics of different fuels in the supersonic combustor and found that their ignition process is similar, but the frequency of the flame oscillations depends on the fuel type. Li and Qiao 10 studied the effect of inlet conditions on the ignition and flame stabilization of the supersonic combustion chamber and showed that the air throttling may help to achieve the flame stabilization for the Mach numbers more than 4.…”

Section: Introductionmentioning

confidence: 99%

Combustion efficiency and pressure loss balance for the supersonic combustor

Tahsini

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The purpose of this paper is to investigate the effects of intake’s compression process of the scramjet on its flight performance. The hydrogen injection to the supersonic cross-flow is considered as the problem configuration. The finite volume solver is developed to simulate the compressible reacting turbulent flow using the proper reaction mechanism as the finite rate chemistry. The combustion efficiency and the drag force are the most important parameters on the scramjet flight performance, and finding the design point to balance the higher combustion efficiency and the lower minimum drag, which depends on the total pressure loss, can be used to optimize the supersonic combustors. The performance of the supersonic intake is considered here using some oblique shock waves with equal flow-deflection angles to compute the combustor’s inlet condition. The variation of combustion efficiency and total pressure loss is presented for different combustor’s inlet conditions. The results are presented for the constant jet to inlet pressure ratios and also for the constant equivalence ratios, in which the last one is much appropriate and utilized to find the optimum design point of the intake and the combustor, for assumed flight condition.

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Investigation of flow and combustion characteristics in a hydrogen-fueled scramjet combustor

Yan,

Tian,

et al. 2024

J Braz. Soc. Mech. Sci. Eng.

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Experimental study on the effects of simulated flight conditions on ignition and flame stabilization in a supersonic combustor

Cited by 25 publications

References 26 publications

Inlet air and fuel flow pressure fluctuation effect on supersonic combustion

Inlet air and fuel flow pressure fluctuation effect on supersonic combustion

Combustion efficiency and pressure loss balance for the supersonic combustor

Investigation of flow and combustion characteristics in a hydrogen-fueled scramjet combustor

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