Civil turbofan engine exhaust aerodynamics: impact of fan exit flow characteristics

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dc.contributor.authorGoulos, Ioannis
dc.contributor.authorMacManus, David G.
dc.date.accessioned2019-08-01T14:43:15Z
dc.date.available2019-08-01T14:43:15Z
dc.date.issued2019-05-17
dc.description.abstractIt is envisaged that future civil aero-engines will operate with greater bypass ratios compared to contemporary configurations to lower specific thrust and improve propulsive efficiency. This trend is likely to be accompanied with the implementation of a shorter nacelle and bypass duct for larger engines. However, a short bypass duct may result in an aerodynamic coupling between the exit flow conditions of the fan Outlet Guide Vanes (OGVs) and the exhaust system. Thus, it is imperative that the design of the exhaust is carried out in combination with the fan exit profile. A parabolic definition is used to parameterise and control the circumferentially-averaged radial profiles of stagnation pressure and temperature at the fan OGV exit. The developed formulation is coupled with a parametric exhaust design approach, an automatic computational mesh generator, and a compressible ow solution method. A global optimisation strategy is devised comprising methods for Design of Experiment (DOE), Response Surface Modelling (RSM), and genetic optimisation. A combined Design Space Exploration (DSE) comprising both geometric, as well as fan exit profile variables, is performed to optimise the exhaust geometry in conjunction with the fan exit profile. The developed approach is used to derive optimum exhaust geometries for a tip, mid, and hub-biased fan blade loading distribution. It is shown that the proposed formulation can ameliorate adverse transonic flow characteristics on the core after-body due to a non-uniform bypass inflow. The hub-loaded profile was found to be most penalising in terms of exhaust performance compared to the mid and tip-loaded variants. It is demonstrated that the combined fan exit profile and exhaust geometry optimisation offers significant performance improvement compared to the fixed inflow cases. The predicted performance benefits can reach up to 0.19% in terms of exhaust velocity coefficient, depending on fan loading characteristics. A notable improvement is also noted in terms of bypass nozzle discharge coefficient. This suggests that the combined optimisation can lead to an exhaust design that can satisfy the engine mass-flow rate demand with a reduced geometric throat area, thus potentially offering further exhaust size and weight benefits.en_UK
dc.identifier.citationGoulos I, MacManus D, Sheaf C. Civil turbofan engine exhaust aerodynamics: impact of fan exit flow characteristics. Aerospace Science and Technology, Volume 93, October 2019, Article number 105181en_UK
dc.identifier.cris23450332
dc.identifier.issn1270-9638
dc.identifier.urihttps://doi.org/10.1016/j.ast.2019.05.033
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/14407
dc.language.isoenen_UK
dc.publisherElsevieren_UK
dc.rightsAttribution-NonCommercial-NoDerivatives 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/4.0/*
dc.subjectTurbofanen_UK
dc.subjectAerodynamicsen_UK
dc.subjectComputational fluid dynamicsen_UK
dc.subjectPropulsion integrationen_UK
dc.subjectClass-shape transformationen_UK
dc.subjectFan outlet guide vaneen_UK
dc.subjectExhaust nozzlesen_UK
dc.subjectDesign optimisationen_UK
dc.titleCivil turbofan engine exhaust aerodynamics: impact of fan exit flow characteristicsen_UK
dc.typeArticleen_UK

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