Engine mounting systems and methods that reduce engine core bending provide a first forward mount (130) connectable to a forward part of an engine core of an aircraft, an aft mount (150) connectable to an aft part of the core, and in a variant a second forward mount (140) connectable to the engine radially outward from the longitudinal axis of the engine with respect to the first forward mount, e.g. to a fan casing. The first forward mount reacts forces in a longitudinal, a lateral and a vertical direction. The aft mount reacts forces in the lateral direction and moments about the longitudinal direction, and in a variant vertical forces only from a predetermined pitch deflection of the engine. Stiffness values of the (first) forward and/or aft mount in the vertical direction may be reduced upon a fan blade off event. Where present, the second forward mount reacts forces in the longitudinal direction by being offset from the first forward mount such that reacting forces in the longitudinal direction by the forwards mounts reacts moments about the lateral direction.
MOUNTING SYSTEMS, DEVICES, AND METHODS FOR AIRCRAFT ENGINES
2021-09-16
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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