Study on cooling inerting of an airborne fuel tank in flight

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.

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