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Study on cooling inerting of an airborne fuel tank in flight

Guannan Liu (College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China)
Liqun Wang (College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China)
Hongming Wang (College of Marine Electrical and Intelligent Engineering, Jiangsu Maritime Institute, Nanjing, China)
Long Huang (College of Marine Electrical and Intelligent Engineering, Jiangsu Maritime Institute, Nanjing, China)
Hao Peng (State Key Laboratory of Marine Resource Utilization in South China Sea, Shanghai Maritime University, Shanghai, China)
Shiyu Feng (College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 18 April 2022

Issue publication date: 5 December 2022

98

Abstract

Purpose

This study aims to seek a new economic and environmental protection fuel tank inerting method.

Design/methodology/approach

The principle that serves as the basis for the cooling inerting process is described, the workflow of the cooling inerting system is designed, the mathematical model of the cooling inerting system is established, and the important performance changes of cooling inerting in the flight package line and the influence of key parameters on it are simulated by using Modelica software.

Findings

The results show that the cooling inerting system can be turned on to quickly reduce the vapour concentration in the gas phase in the fuel space and reduce the temperature below the flammability limit. Within a certain range of pumping flow, the inerting effect is more obvious when the pumping flow is larger. Simply running the cooling inerting system on the ground can remain the tank in an inert state throughout the flight envelope.

Research limitations/implications

However, cooling inerting is suitable for models with fewer internal heat sources. An excessive number of internal heat sources will lead to inerting failure.

Originality/value

This study provides theoretical support for the feasibility of cooling inerting. Cooling inerting does not require engine air, and the cooling is mainly accomplished with air, which places a small load on the cooling system and has a much lower cost than the airborne hollow fibre film inerting technology widely used at present. It is a promising new inerting technology.

Keywords

Acknowledgements

This study was supported by the National Natural Science Foundation of China Civil Aviation Joint Fund (No. U1933121). Interdisciplinary Innovation Foundation for Graduates, NUAA (No. KXKCXJJ202004). Graduate Research and Practice Innovation Program of Nanjing University of Aeronautics and Astronautics (xcxjh20210108). The Fundamental Research Funds for the Central Universities. Priority Academic Program Development of Jiangsu Higher Education Institutions.

Data availability statement: Some or all data, models, or code that support the findings of this study are available from the corresponding author upon reasonable request.

Citation

Liu, G., Wang, L., Wang, H., Huang, L., Peng, H. and Feng, S. (2022), "Study on cooling inerting of an airborne fuel tank in flight", Aircraft Engineering and Aerospace Technology, Vol. 94 No. 10, pp. 1628-1635. https://doi.org/10.1108/AEAT-08-2021-0263

Publisher

:

Emerald Publishing Limited

Copyright © 2022, Emerald Publishing Limited

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