View in EDS

Simulation of the refuelling process for an LH2-powered commercial aircraft part 1 - Modelling and validation.

Saved in:
Bibliographic Details
Title: Simulation of the refuelling process for an LH2-powered commercial aircraft part 1 - Modelling and validation.
Authors: ten Damme, L.1 (AUTHOR), van Put, M.2 (AUTHOR), Gangoli Rao, A.1 (AUTHOR) a.gangolirao@tudelft.nl
Source: International Journal of Hydrogen Energy. Dec2025, Vol. 195, pN.PAG-N.PAG. 1p.
Subjects: Liquid hydrogen, Model validation, Heat transfer, Computer simulation, Low temperature engineering, Fueling, Commercial aeronautics
Abstract: Liquid hydrogen (LH 2) is a promising candidate for zero emission aviation, but its cryogenic properties make the refuelling process fundamentally different from that of conventional jet fuels. Although previous studies have addressed LH 2 storage and system integration, detailed modelling of the refuelling process remains limited. This paper presents the first part of a two-part study focused on simulation of the refuelling process for an LH 2 -powered commercial aircraft. An existing tank model is substantially modified to more accurately capture relevant physical phenomena, including heat transfer and droplet dynamics during top-fill spray injection. Newly available experimental data on LH 2 no-vent filling enables direct validation of the model under conditions that match the experimental setup. A sensitivity analysis identifies the most influential parameters that affect model precision, including loss coefficient, droplet diameter, radiative heat ingress, and vent-closing pressure. The validated model forms the basis for Part 2 of this study, in which it is applied to a representative LH 2 -powered commercial aircraft to simulate refuelling times, quantify venting losses, and assess the impact of key operational settings. These results support the design of efficient LH 2 refuelling systems for future aircraft and airport infrastructure. • A detailed mathematical model on the cryogenic refuelling process. • Spray droplet model taken into account. • The model compares well with cryogenic experiment of NASA. • The vent pressure has significant influence on the refuelling time. [ABSTRACT FROM AUTHOR]
Copyright of International Journal of Hydrogen Energy is the property of Pergamon Press - An Imprint of Elsevier Science and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
Description
Abstract:Liquid hydrogen (LH 2) is a promising candidate for zero emission aviation, but its cryogenic properties make the refuelling process fundamentally different from that of conventional jet fuels. Although previous studies have addressed LH 2 storage and system integration, detailed modelling of the refuelling process remains limited. This paper presents the first part of a two-part study focused on simulation of the refuelling process for an LH 2 -powered commercial aircraft. An existing tank model is substantially modified to more accurately capture relevant physical phenomena, including heat transfer and droplet dynamics during top-fill spray injection. Newly available experimental data on LH 2 no-vent filling enables direct validation of the model under conditions that match the experimental setup. A sensitivity analysis identifies the most influential parameters that affect model precision, including loss coefficient, droplet diameter, radiative heat ingress, and vent-closing pressure. The validated model forms the basis for Part 2 of this study, in which it is applied to a representative LH 2 -powered commercial aircraft to simulate refuelling times, quantify venting losses, and assess the impact of key operational settings. These results support the design of efficient LH 2 refuelling systems for future aircraft and airport infrastructure. • A detailed mathematical model on the cryogenic refuelling process. • Spray droplet model taken into account. • The model compares well with cryogenic experiment of NASA. • The vent pressure has significant influence on the refuelling time. [ABSTRACT FROM AUTHOR]
ISSN:03603199
DOI:10.1016/j.ijhydene.2025.152168