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Publishing Language: Chinese

Research on oxygen consumption based inerting monolithic catalyst reactor performance

Chenyang GUO1, Yi LIU2, Haozheng LIU1, Junjie WANG1, jingcheng GAO1, Shiyu FENG1( )
Key Laboratory of Aircraft Environment and Life Support of Ministry of Industry and Information Technology,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration,Jincheng Nanjing Engineering Institute of Aircraft System,Aviation Industry Corporation of China,Nanjing 211106,China
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Abstract

An experiment of Pd/γ-Al2O3 performance is carried out to get its reaction dynamics function. A two-dimensional monolithic catalyst transient model is established and solved with Modelica. Catalyst transition performance has been studied by simulation. The influence of high temperature and catalyst deactivation on a monolithic catalyst is researched. It was investigated how the reactor was affected by the oxygen content while in flight. The result shows that wall cooling can reduce high temperatures and reactor efficiency at the same time. The catalyst deactivation due to high temperature occurs on the surface near the outlet of the reactor, where the sharpest reaction takes place. Deactivation in Less than half of the catalyst surface area cuts down the efficiency by 80%. The conversion rate of fuel steam can be effectively increased by the increase in oxygen concentration brought on by the loss of pressure during aircraft ascent; however, precautions should be taken to prevent the acceleration of catalyst deactivation caused by high oxygen concentration.

CLC number: V228 Document code: A Article ID: 1001-5965(2025)10-3547-08

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Journal of Beijing University of Aeronautics and Astronautics
Pages 3547-3554

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Cite this article:
GUO C, LIU Y, LIU H, et al. Research on oxygen consumption based inerting monolithic catalyst reactor performance. Journal of Beijing University of Aeronautics and Astronautics, 2025, 51(10): 3547-3554. https://doi.org/10.13700/j.bh.1001-5965.2023.0562

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Received: 01 September 2023
Published: 15 August 2024
© Journal of Beijing University of Aeronautics and Astronautics