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2021 | OriginalPaper | Buchkapitel

Aerodynamics and Loss Accounting of a Low Pressure Ratio Fan for an Over-Wing Mounted Engine

verfasst von : Daniel Giesecke, Jens Friedrichs

Erschienen in: Fundamentals of High Lift for Future Civil Aircraft

Verlag: Springer International Publishing

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Abstract

In recent research, several Boundary Layer Ingesting propulsors concepts have been investigated with varying degrees of airframe integration. The contribution compares the well-known approach of a \(60^\circ \) circumferential inlet distortion with a configuration of a partly wing-embedded and a fully embedded engine integration. The second type is characterized by a local distortion while the whole flow field of the third shows flow variations. Conventional distortion metrics are getting close to their limits for an adequate assessment. The focus of this contribution lies in highlighting differences in loss generation through the fan stage and at dedicated stations. The stator blade row has a changing role in terms of entropy production, depending on the distortion type. Concepts for a stator refitting are presented and successfully applied. Almost one-third of efficiency drop is recovered for the final design change.

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Vorheriges Kapitel Air Curtain Flow Control for Aerodynamic Noise Reduction

Nächstes Kapitel Aerodynamic Optimization of the OWN Configurations REF3 and REF4 in Cruise Flight

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Titel: Aerodynamics and Loss Accounting of a Low Pressure Ratio Fan for an Over-Wing Mounted Engine
verfasst von: Daniel Giesecke
Jens Friedrichs
Verlag: Springer International Publishing
Buch: Fundamentals of High Lift for Future Civil Aircraft
Print ISBN: 978-3-030-52428-9

Electronic ISBN: 978-3-030-52429-6

Copyright-Jahr: 2021
DOI: https://doi.org/10.1007/978-3-030-52429-6_19

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