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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Abstract	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.
AbstractList	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. 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.
Author	Le, Jialing Liu, Yuan Shi, Wen Zhang, Chenlin Tian, Ye Guo, Mingming
Author_xml	– sequence: 1 givenname: Ye orcidid: 0000-0001-9955-3438 surname: Tian fullname: Tian, Ye email: tianye@cardc.cn organization: Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang, 621000, China – sequence: 2 givenname: Wen surname: Shi fullname: Shi, Wen organization: Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang, 621000, China – sequence: 3 givenname: Mingming surname: Guo fullname: Guo, Mingming organization: Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang, 621000, China – sequence: 4 givenname: Yuan surname: Liu fullname: Liu, Yuan organization: Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang, 621000, China – sequence: 5 givenname: Chenlin surname: Zhang fullname: Zhang, Chenlin organization: Shenyang Aircraft Design and Research Institute, Shenyang, 110035, China – sequence: 6 givenname: Jialing surname: Le fullname: Le, Jialing organization: Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang, 621000, China
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Snippet	The combustion characteristics of a hydrogen-fueled scramjet combustor were investigated experimentally and numerically. One nonreacting case (case 1), and two...
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SubjectTerms	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
Title	Investigation of combustion characteristics in a hydrogen-fueled scramjet combustor
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