| Effect of pilot hydrogen on the mixing and combustion characteristics in kerosene-fueled scramjet | |
| Shi, HongQing1,2; Wang, Du2; Cui NF(崔乃夫)3; Zhao, ChenYang2; Lei, JieMing2; Zhu, ZiQiang2; Zhang, YaNing1; Tian, ZhenYu2,4,5 | |
| Corresponding Author | Tian, Zhen-Yu([email protected]) |
| Source Publication | APPLIED THERMAL ENGINEERING
 |
| 2025 | |
| Volume | 258Pages:10 |
| ISSN | 1359-4311 |
| Abstract | Scramjet engine has presented excellent advantages in hypersonic flight due to its excellent flight performance, such as simple structure, high specific impulse performance and a broad range of cruising speed. However, the stable combustion is extremely formidable in the case of supersonic flow. This work combined several flameholding strategies, i.e., vertical injection orifices, dual cavities, pilot flame, as well as converting kerosene as supercritical state, aiming at providing a significant reference for the supersonic stable combustion. Meanwhile, as a highly reactive fuel, the effects of hydrogen addition on the mixing and combustion characteristics were investigated in detail. In the process, the total equivalence ratio of kerosene and pilot hydrogen was held constant at 0.8, and the effect of different equivalence ratios of hydrogen (ERH = 0, 0.34 and 0.47) was investigated. The results showed that the addition of hydrogen can effectively enhance the combustion intensity in the combustor. The wall static pressure reached from 230 kPa to 259 kPa with ERH increasing from 0 to 0.47. High pilot hydrogen can make the back pressure propagate toward the entrance, improving the risk to compromise the stable inlet conditions. The shock wave disk was occurred near the entrance, leading to the drastic variation of pressure, temperature and density. The consumption of supercritical kerosene was very fast, while the combustion of hydrogen was relatively lower, even uncomplete burning of hydrogen was observed at exit. With the addition of pilot hydrogen, the heat released in the combustor became less. Specifically, as the ERH increased from 0 to 0.47, the heat released in combustor reduced from 4.1 x 104 to 3.2 x 104 MJ/s, resulting in the corresponding temperature at the exit decreaing from 1777 to 1607 K, due to the decrement of combustion efficiency resulted from the addition of hydrogen. |
| Keyword | Scramjet Pilot hydrogen Dual cavities Mixing efficiency Combustion performance |
| DOI | 10.1016/j.applthermaleng.2024.124670 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:001344547300001 |
| WOS Keyword | FLAME STABILIZATION ; IGNITION CHARACTERISTICS ; SUPERSONIC COMBUSTOR ; NUMERICAL-ANALYSIS ; RP-3 KEROSENE ; CAVITY ; INJECTION ; MODE |
| WOS Research Area | Thermodynamics ; Energy & Fuels ; Engineering ; Mechanics |
| WOS Subject | Thermodynamics ; Energy & Fuels ; Engineering, Mechanical ; Mechanics |
| Funding Project | NSFC[52325604] ; MOST[2022YFB4003900/2021YFA0716200] ; National Science and Technology Major Project[J2019-III-0050-0048] ; CAS Project for Young Scientists in Basic Research[YSBR-028] ; Innovation Academy for Light-duty Gas Turbine, Chinese Academy of Sciences, Innovation guidance youth project[CXYJJ21-QN-001] |
| Funding Organization | NSFC ; MOST ; National Science and Technology Major Project ; CAS Project for Young Scientists in Basic Research ; Innovation Academy for Light-duty Gas Turbine, Chinese Academy of Sciences, Innovation guidance youth project |
| Classification | 一类 |
| Ranking | 3+ |
| Contributor | Tian, Zhen-Yu |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/97152 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Harbin Inst Technol, Sch Energy Sci & Engn, Harbin 150001, Peoples R China; 2.Chinese Acad Sci, Inst Engn Thermophys, Beijing 100190, Peoples R China; 3.Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Inst Mech, Beijing 100190, Peoples R China; 4.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100190, Peoples R China; 5.Chinese Acad Sci, Inst Engn Thermophys, State Key Lab Coal Convers, Beijing 100190, Peoples R China |
| Recommended Citation GB/T 7714 | Shi, HongQing,Wang, Du,Cui NF,et al. Effect of pilot hydrogen on the mixing and combustion characteristics in kerosene-fueled scramjet[J]. APPLIED THERMAL ENGINEERING,2025,258:10.Rp_Au:Tian, Zhen-Yu |
| APA | Shi, HongQing.,Wang, Du.,崔乃夫.,Zhao, ChenYang.,Lei, JieMing.,...&Tian, ZhenYu.(2025).Effect of pilot hydrogen on the mixing and combustion characteristics in kerosene-fueled scramjet.APPLIED THERMAL ENGINEERING,258,10. |
| MLA | Shi, HongQing,et al."Effect of pilot hydrogen on the mixing and combustion characteristics in kerosene-fueled scramjet".APPLIED THERMAL ENGINEERING 258(2025):10. |
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