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Jungho Lee, Ingyu Lee, Seongphil Woo, Yeoungmin Han and Youngbin Yoon
The spray and combustion characteristics of a gas-centered swirl coaxial (GCSC) injector used in oxidizer-rich staged combustion cycle engines were analyzed. The study focused on varying the recess ratio, presence of gas swirl, and swirl direction to imp...
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Ulrich Carsten Johannes Rischmüller, Alexandros Lessis, Patrick Egerer and Mirko Hornung
A wide range of aircraft propulsion technologies is being investigated in current research to reduce the environmental impact of commercial aviation. As the implementation of purely hydrogen-powered aircraft may encounter various challenges on the airpor...
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Yongsheng Zhao, Junfei Wu and Xiangyang Mu
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Stanislav Karpuk, Yiyuan Ma and Ali Elham
Present work investigates the potential of a long-range commercial blended wing body configuration powered by hydrogen combustion engines with future airframe and propulsion technologies. Future technologies include advanced materials, load alleviation t...
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Chuang Zhou, Nanjia Yu, Shuwen Wang, Shutao Han, Haojie Gong, Guobiao Cai and Jue Wang
Liquid rocket engines with hydrogen peroxide and kerosene have the advantages of high density specific impulse, high reliability, and no ignition system. At present, the cooling problem of hydrogen peroxide engines, especially with regenerative cooling, ...
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Yuankun Zhang, Qingjun Zhao, Bin Hu, Qiang Shi, Wei Zhao and Xiaorong Xiang
This paper presents a numerical simulation analysis of the flow and combustion characteristics of a fuel-rich LOX (liquid oxygen)/kerosene gas generator in an ATR (air turbo rocket) engine, examining the effects of local parameters on the combustion flow...
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Artur Kulaszka, Józef Blachnio and Henryk Borowczyk
The reliability and operational safety of an aircraft engine gas turbine are extremely important in terms of its operation. In the course of operation, these turbines undergo complex thermal, mechanical, aerodynamic, and chemical exhaust gas loads. Due t...
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Yang Liu, Xintong Li, Pengcheng Wang, Xiaotian Zhang, Hao Zhu and Guobiao Cai
This paper proposed a multi-objective, multi-disciplinary design optimization and multi-attribute evaluation method for the manned lunar lander descent stage. A system design model is established considering multiple disciplines such as propulsion, struc...
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Valerio Marciello, Mario Di Stasio, Manuela Ruocco, Vittorio Trifari, Fabrizio Nicolosi, Markus Meindl, Bruno Lemoine and Priscilla Caliandro
The environmental impact of aviation in terms of noise and pollutant emissions has gained public attention in the last few years. In addition, the foreseen financial benefits of an increased energy efficiency have motivated the transport industry to inve...
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Jian Liu, Mengyao Xu, Pengchao Liu and Wenxiong Xi
At an extremely high Mach number, the regenerative cooling of traditional kerosene cannot meet the requirement of the heat sink caused by aerodynamic heating and internal combustion in a scramjet propulsion system. As a supplement of traditional regenera...
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