Discrete particle simulation for the initial stages of ice accretion in aircraft engines: initial model development
Paper
Paper/Presentation Title | Discrete particle simulation for the initial stages of ice accretion in aircraft engines: initial model development |
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Presentation Type | Paper |
Authors | Buttsworth, David (Author), Saleh, Khalid (Author) and Yusaf, Talal (Author) |
Editors | Abidin, Izham Bin Datuk Zainal |
Journal or Proceedings Title | Proceedings of the 3rd International Conference on Energy and Environment (ICEE 2009) |
ERA Conference ID | 50682 |
Number of Pages | 4 |
Year | 2009 |
Place of Publication | Piscataway, NJ. United States |
ISBN | 9781424451456 |
Digital Object Identifier (DOI) | https://doi.org/10.1109/ICEENVIRON.2009.5398655 |
Web Address (URL) of Paper | http://ieeexplore.ieee.org/stamp/stamp.jsp?tp=&arnumber=5398655&isnumber=5398594 |
Conference/Event | 3rd International Conference on Energy and Environment (ICEE 2009): Advancement Towards Global Sustainability |
International Conference on Energy & Environment | |
Event Details | 3rd International Conference on Energy and Environment (ICEE 2009): Advancement Towards Global Sustainability Event Date 07 to end of 08 Dec 2009 Event Location Malacca, Malaysia |
Event Details | International Conference on Energy & Environment EE |
Abstract | Elements of a discrete particle model that might find application in aircraft engine icing studies are introduced in this paper. As it currently stands, the model is in an embryonic state but it does provides a framework from which further developments can easily proceed. It provides a convenient basis for assessment of aerodynamic particle drag, surface friction, heat transfer and other effects likely to be relevant in the engine icing problem. The model treats the initial stage of accretion, before the inviscid stagnation point flow field is measurably affected by the presence of the ice build-up. The intention is to provide an indication flow field and surface conditions that are likely to lead to stable accretion of ice prior to detectable changes in the aerodynamics of the stagnation point flow field. Preliminary results from the model are presented to demonstrate the current functionality of the model. |
Keywords | aircraft engine icing; ice particle; simulation; aerodynamic particle drag; aircraft engines; discrete particle simulation; embryonic state; engine icing problem; heat transfer; ice accretion; indication flow field; inviscid stagnation point flow field; surface friction |
ANZSRC Field of Research 2020 | 401703. Energy generation, conversion and storage (excl. chemical and electrical) |
460207. Modelling and simulation | |
401204. Computational methods in fluid flow, heat and mass transfer (incl. computational fluid dynamics) | |
Public Notes | © 2009 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other uses, in any current or future media, including reprinting/republishing this material for advertising or promotional purposes, creating new collective works, for resale or redistribution to servers or lists, or reuse of any copyrighted component of this work in other works. |
Byline Affiliations | University of Oxford, United Kingdom |
Faculty of Engineering and Surveying | |
Department of Mechanical and Mechatronic Engineering |
https://research.usq.edu.au/item/9z643/discrete-particle-simulation-for-the-initial-stages-of-ice-accretion-in-aircraft-engines-initial-model-development
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