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Chengfei Tao, Rongyue Sun, Yichen Wang, Yang Gao, Lin Meng, Liangbao Jiao, Shaohua Liang and Ling Chen
This study experimentally explored the effects of equivalence ratio settings on ethanol fuel combustion oscillations with a laboratory-scale combustor. A contrary flame equivalence ratio adjusting trend was selected to investigate the dynamic characteris...
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Arvid Åkerblom, Martin Passad, Alessandro Ercole, Niklas Zettervall, Elna J. K. Nilsson and Christer Fureby
With growing interest in sustainable civil supersonic and hypersonic aviation, there is a need to model the combustion of alternative, sustainable jet fuels. This work presents numerical simulations of several related phenomena, including laminar flames,...
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Giacomo Cinieri, Zubair Ali Shah, Guido Marseglia and Maria Grazia De Giorgi
The research effort in the microcombustor field has recently increased due to the demand for high-performance systems in microelectromechanical and micro power generation devices. To address rising concerns about pollutants from fossil sources, zero-carb...
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Seung-Min Jeong, Hyung-Seok Han, Bu-Kyeng Sung, Wiedae Kim and Jeong-Yeol Choi
This study numerically investigated the combustion instability and characteristics of a laboratory-scale gaseous hydrogen-fueled scramjet combustor. For this purpose, a numerical simulation with an improved detached eddy simulation and a detailed hydroge...
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Bingyue Jia, Yining Zhang, Hao Meng, Fanxiao Meng, Hu Pan and Yanji Hong
Rotating detonation engines (RDEs) are a promising propulsion technology featuring high thermal efficiency and a simple structure. To adapt the practical engineering applications of ramjet RDEs, rotating detonation combustion using a liquid hydrocarbon a...
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Min-Su Kim, In-Hoi Koo, Keon-Hyeong Lee, Eun-Sung Lee, Hyung-Seok Han, Seung-Min Jeong, Holak Kim and Jeong-Yeol Choi
This experimental investigation focused on the ignition and combustion characteristics of a tandem cavity-based scramjet combustor with side-by-side identical cavities. This study utilized the Pusan National University-direct connect scramjet combustor (...
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In-Hoi Koo, Keon-Hyeong Lee, Min-Su Kim, Hyung-Seok Han, Holak Kim and Jeong-Yeol Choi
Fuel injection and mixing affect the characteristics of detonation initiation and propagation, as well as the propulsion performance of rotating detonation engine (RDE). A study on the injector is carried out in the present investigation. A rectangular-s...
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Jinrong Bao, Chenzhen Ji, Deng Pan, Chao Zong, Ziyang Zhang and Tong Zhu
The propagation mechanism of flow disturbance under acoustic excitations plays a crucial role in thermoacoustic instability, especially when considering the effect of non-premixed combustion on heat release due to reactant mixing and diffusion. This rela...
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Jin Gao, Ziyi Kang, Weiheng Sun, Youyin Wang, Junlong Zhang and Wen Bao
With the in-depth research on hypersonic aerodynamics and hypersonic propulsion technology, humans are growing closer to space travel. Recent studies have shown that the pre-cooled air-turborocket (ATR) or turboexpander engines are some of the potential ...
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Xiang Li, Qingchun Lei, Xiaocun Zhao, Wei Fan, Shuang Chen, Li Chen, Ye Tian and Quan Zhou
The combustion characteristics of a hydrogen-fueled supersonic combustor featuring a large cavity length-to-depth ratio (i.e., 11) were examined by performing experimental trials while varying the fuel injector positions and equivalence ratios. During th...
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