Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Application of the “actuator disk” boundary condition to calculation of a non-uniform flow in the air intake of modern turbofan engines

Published: 15.08.2019

Authors: Nguyen V.H.

Published in issue: #8(92)/2019

DOI: 10.18698/2308-6033-2019-8-1909

Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts

As the degree of bypass ratio of modern aviation turbofan engines increases, their appearance and characteristics change as well: the nacelle diameter increases, the air intake length decreases, and the temperature and jet noise reduce. Due to these circumstances, the design must take into account the interaction between the fan and the air intake as part of configuration. An approach based on unsteady three-dimensional modeling with account for full blade tips is necessary for the analysis, but is resource-intensive. In some cases, an approach based on the “actuator disk” boundary condition can be used to study aerodynamic interference. The paper considers a validated computational technique based on the “actuator disk” boundary condition with flow structure in front of the fan taken into account. The results of the computational study of the characteristics of the fan model in the engine nacelle are given, as well as the analysis of options for the “actuator disk” boundary condition and their application to the calculation of a non-uniform flow in the air intake under side wind conditions.

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