Investigation of combustion characteristics in a hydrogen-fueled scramjet combustor

The combustion characteristics of a hydrogen-fueled scramjet combustor were investigated experimentally and numerically. One nonreacting case (case 1), and two different equivalence ratio (ER) reacting cases (cases 2 and 3) were compared. The combustion process of each reacting case was divided into...

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Veröffentlicht in:Acta astronautica Jg. 186; S. 486 - 495
Hauptverfasser: Tian, Ye, Shi, Wen, Guo, Mingming, Liu, Yuan, Zhang, Chenlin, Le, Jialing
Format: Journal Article
Sprache:Englisch
Veröffentlicht: Elmsford Elsevier Ltd 01.09.2021
Elsevier BV
Schlagworte:
Combustion
Combustion chambers
Combustion characteristics
Equivalence ratio
Hydrogen
Hydrogen combustion
Ignition
Laser induced fluorescence
Pressure distribution
Scramjet
Shear layers
Stress concentration
Subsonic combustion
Supersonic combustion
Supersonic combustion ramjet engines
Supersonic combustor
Wall pressure
Supersonic combustor
Combustion characteristics
Hydrogen
Scramjet
Ignition
ISSN:0094-5765, 1879-2030
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Zusammenfassung:The combustion characteristics of a hydrogen-fueled scramjet combustor were investigated experimentally and numerically. One nonreacting case (case 1), and two different equivalence ratio (ER) reacting cases (cases 2 and 3) were compared. The combustion process of each reacting case was divided into three phases. In the first phase, the monitor pressure in case 2 (ER = 0.1) reached a higher level due to the fuel injected before the hydrogen was ignited, whereas the change in case 3 (ER = 0.3) was the opposite, being less than that in the nonreacting flow. Almost all of the hydrogen in case 2 was in the front of the cavity, and that in case 3 was both throughout the whole cavity and near the top wall behind the cavity. In the second phase, the ignition times were about 0.010 s in case 2 and about 0.022 in case 3; a larger ER of hydrogen might be difficult to ignite. Finally, in the last phase, the hydrogen combustion was stable. The shock train in case 3 was pushed into the isolator, and the disturbing distance was about 0.08 m, in accordance with the wall pressure distribution. The higher static temperature in case 2 was mainly in the back of the cavity and that in case 3 was in the cavity shear layer, in line with the hydroxyl planner laser-induced fluorescence (OH-PLIF) results. The combustion mode in case 2 was supersonic combustion and that in case 3 was subsonic combustion. •Combustion characteristics were investigated in a supersonic combustor.•The whole combustion process could be divided into three parts.•Various measurements are used for better understanding combustion characteristics.•The ignition time for different ER reacting cases was measured.
Bibliographie:ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 14
ISSN:0094-5765
1879-2030
DOI:10.1016/j.actaastro.2021.06.021