Fan flow field in an installed variable pitch fan operating in reverse thrust for a range of aircraft landing speeds

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dc.contributor.authorRajendran, David John
dc.contributor.authorPachidis, Vassilios
dc.date.accessioned2020-01-29T12:47:00Z
dc.date.available2020-01-29T12:47:00Z
dc.date.issued2019-09-20
dc.description.abstractThe installed flow field for a Variable Pitch Fan (VPF) operating in reverse thrust for the complete aircraft landing run is described in this paper. To do this, a VPF design to generate reverse thrust by reversing airflow direction is developed for a representative 40000 lbf modern high bypass ratio engine. Thereafter, to represent the actual flow conditions that the VPF would face, an engine model that includes the nacelle, core inlet splitter, outlet guide vanes, bypass nozzle, core exhaust duct, aft-body plug and core nozzle is designed. The engine model with the VPF is attached to a representative airframe in landing configuration to include the effects of installation. A rolling ground plane that mimics the runway during the landing run is also included to complete the model definition. 3D RANS solutions are carried out for two different VPF stagger angle settings and rotational speeds to obtain the fan flow field. The dynamic installed VPF flow field is characterized by the interaction of the free stream and the reverse stream flows. The two streams meet in a shear layer in the fan passages and get deflected radially outwards before turning back onto themselves. The flow field changes with stagger setting, fan rotational speed and the aircraft landing speed because of the consequent changes in the momentum of the two streams. The description of the installed VPF flow field as generated in this study is necessary to: a) qualify VPF designs that are typically designed by considering only the uninstalled static flow field b) choose the VPF operating setting for different stages of the aircraft landing run.en_UK
dc.identifier.citationRajendran DJ, Pachidis V. (2019) Fan flow field in an installed variable pitch fan operating in reverse thrust for a range of aircraft landing speeds. Journal of Engineering for Gas Turbines and Power, Volume 141, Issue 10, October 2019, Article number 101018en_UK
dc.identifier.cris23850813
dc.identifier.issn0742-4795
dc.identifier.urihttps://doi.org/10.1115/1.4044686
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/15041
dc.language.isoenen_UK
dc.publisherASMEen_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectAircraft, Flow (Dynamics)en_UK
dc.subjectReynolds-averaged Navier–Stokes equationsen_UK
dc.subjectShear (Mechanics)en_UK
dc.subjectThrusten_UK
dc.subjectNozzlesen_UK
dc.subjectDuctsen_UK
dc.subjectEnginesen_UK
dc.subjectGuide vanesen_UK
dc.subjectExhaust systemsen_UK
dc.titleFan flow field in an installed variable pitch fan operating in reverse thrust for a range of aircraft landing speedsen_UK
dc.typeArticleen_UK

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