The design of an intake for a gas turbine engine involves CFD-based investigation and experimental assessment in an intake test\r\nrig. In both cases, the engine is represented by a mass flux sink, usually positioned a fewfan radii aft of the real fan face. In general,\r\nthis approach is sufficient to analyze intake geometry for low distortion at the fan face, because in this case the interaction of the\r\nfan with the inlet flow can be neglected. Where there are higher levels of distortion at the fan face, the interaction could become\r\nmore significant and a different approach would be preferable. One alternative that takes into account the interaction in such cases\r\nincludes the fan in the analysis of the intake, using either a steady or unsteady flow model approach. However, this solution is\r\nexpensive and too computationally intensive to be useful in design mode. The solution proposed in this paper is to implement\r\na new boundary condition at the fan face which better represents the interaction of the fan with the flow in the air intake in the\r\npresence of distortion. This boundary condition includes a simplified fanmodel and a coupling strategy applied between the fan and\r\nthe inlet. The results obtained with this new boundary condition are compared to full 3D unsteady CFD simulations that include\r\nthe fan.
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