TURBOFAN ENGINE INCLUDING A FAN ACTUATION SYSTEM

Abstract: a turbofan engine for an aircraft includes a fan and a fan actuation system. the fan has a plurality of fan blades coupled to a fan shaft having one or more fan bearings. the fan blades are rotatable about a pitch axis. the fan actuation system is disposed within a fan hub and includes one or more actuators for rotating the fan blades about the pitch axis and one or more radial thrust bearings. the fan actuation system is characterized by a fan actuation system length envelope in a range of 8.5 to 24 and given by

Inventor(s): Randy M. Vondrell, Keith A. Miedema

CPC Classification: F04D29/362 (NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps ; ion pumps ; electrodynamic pumps ))

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