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Sara Bonuso, Pasquale Di Gloria, Guido Marseglia, Ramón A. Otón Martínez, Ghazanfar Mehdi, Zubair Ali Shah, Antonio Ficarella and Maria Grazia De Giorgi
This study introduces an innovative approach involving the injection of hydrogen into a low-swirl, non-premixed flame, which operates with gaseous fuels derived from an air-blast atomizer designed for aero-engine applications. The aim is to characterize ...
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Christian Paravan, Anwer Hashish and Valerio Santolini
Hybrid rocket engines (HREs) offer a low-cost, reliable, and environmentally friendly solution for both launch and in-space applications. Hybrid propellants have been identified as green thanks to their use of non-toxic, non-carcinogenic oxidizers. Of pa...
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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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Dunhui Xu, Fang Wang, Shengji Li, Xuefeng Huang, Heping Li and Yanhui Guo
To solve the problems associated with micron-sized aluminum (Al), including sintering, agglomeration, and slag deposition during the combustion of aluminized propellants, aluminum?lithium (Al-Li) alloy, prepared by introducing a small amount of Li (1.0 w...
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Zijian Zhang and Ziqi Jiang
Detonation initiation is a prerequisite to normal operations of an oblique detonation engine (ODE), and initiation-assistant measures are imperative in cases of initiation failure that occur in a length-limited combustor under wide-range flight condition...
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Md. Amzad Hossain, Md Nawshad Arslan Islam, Martin De La Torre, Arturo Acosta Zamora and Ahsan Choudhuri
This paper presents the flow and flame characteristics of a highly turbulent reactive flow over a backward-facing step inside a windowed combustor. Flow and combustion experiments were performed at Re = 15,000 and Re = 30,000 using high-resolution 10 kHz...
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Sohaib Khan, Muhammad Umer Sohail, Ihtzaz Qamar, Muzna Tariq and Raees Fida Swati
Thrust regulation is applied to maintain the performance of the liquid propellant rocket engine. The thrust level of a rocket engine can be readily controlled by adjusting the number of propellants introduced into the combustion chamber. In this study, a...
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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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Lei Niu, Hongmao Tu, Haiping Dong and Nan Yan
A functional reliability simulation method based on the Kriging model is proposed to efficiently evaluate the functional reliability of low-shock separation nuts. First, a deterministic separation function simulation model of the separation nut is establ...
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Jiaqi Nan, Jingxuan Li and Lijun Yang
Cylindrical ducts with axial mean temperature gradient and mean flows are typical elements in rocket engines, can combustors, and afterburners. Accurate analytical solutions for the acoustic waves of the longitudinal and transverse modes within these duc...
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