Ignition dynamics and combustion mode transitions in a rocket-based combined cycle combustor operating in the ramjet/scramjet mode

An, Bin; Wang, Zhenguo; Sun, Mingbo

doi:10.1016/j.ast.2021.106951

Cited by 13 publications

(1 citation statement)

References 32 publications

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“…Favorable ignition performance is also an important index for measuring combustor performance. Lefebvre et al conducted a significant number of investigations on the ignition performance of a combustor [15][16][17]. Based on the model of the premixed combustion chamber, the authors investigated both ignition and flame propagation mechanisms and extracted the characteristics at different development phases of ignition [18].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Flame Chemiluminescence and Flow Characteristics of a Reverse-Flow Combustor

et al. 2022

International Journal of Aerospace Engineering

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The reverse-flow combustor is extensively applied in small engines due to its compact structure. The cold-state flow characteristics, the ignition process, and flame chemiluminescence characteristics of the reserve-flow combustor were investigated experimentally. Using the particle imaging velocimeter, the cold-state time-averaged flow fields at three different total pressure loss coefficients ζ B are examined. The ignition processes of the combustor, as well as flame characteristics during stable combustion at different equivalent ratios φ , are analyzed based on flame chemiluminescence imaging when ζ B is 3%. As ζ B increases from 1% to 5%, the flow field of the combustor remains almost unchanged while the flow velocity increases. For ζ B =3%, the ignition time T drops from 26 ms to 16 ms with an increase of φ . In addition, the ignition performance is enhanced. Proportions of the T2 phase (quasi-stable phase) are 73%, 68%, and 66%, respectively, suggesting that the quasi-stable phase is the key to successful ignition. As φ increases, the flame becomes thinner and shorter. Furthermore, standard deviations of continuous image areas of CH ∗ and OH ∗ drop from 0.0143 and 0.0132 to 0.0115 and 0.0109, respectively, which indicates the enhancement of combustion stability. According to the brightness distributions of CH ∗ and OH ∗ along the axial direction of the combustor at different equivalent ratios, the production of OH ∗ is significantly affected by the temperature. It can be adopted as an important sign of heat release during combustion.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Flame Chemiluminescence and Flow Characteristics of a Reverse-Flow Combustor

et al. 2022

International Journal of Aerospace Engineering

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Numerical study on the dynamic process of ramjet/scramjet mode transition in the integrated full flow path for RBCC engine

Liu

Xue

et al. 2023

Applied Thermal Engineering

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Combustion performance of an evaporative flameholder under subsonic-supersonic mixing inflow

Huang,

Zhu,

Zhao

et al. 2025

Applied Thermal Engineering

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Ignition dynamics and combustion mode transitions in a rocket-based combined cycle combustor operating in the ramjet/scramjet mode

Cited by 13 publications

References 32 publications

Experimental Investigation on Flame Chemiluminescence and Flow Characteristics of a Reverse-Flow Combustor

Experimental Investigation on Flame Chemiluminescence and Flow Characteristics of a Reverse-Flow Combustor

Numerical study on the dynamic process of ramjet/scramjet mode transition in the integrated full flow path for RBCC engine

Combustion performance of an evaporative flameholder under subsonic-supersonic mixing inflow

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