Ge Avio S.r.l.

Davide Lercara

Andrea Piazza

Miriam Manzoni

Andrea Donnini

Alessandro Bordoni

A gear assembly of an aircraft including an engine is generally provided. The gear assembly includes a first gear meshed with a second gear to define a gear mesh, and a walled lubricant tank defining a lubricant reservoir and a reservoir inlet opening. The reservoir inlet opening is defined adjacent to an out-of-mesh side of the gear mesh. At least a portion of lubricant from the gear mesh enters the lubricant reservoir through the reservoir inlet opening.

System and method for emergency lubricant flow at an aircraft gear assembly

A fan blade support assembly for an aircraft is generally disclosed. The fan blade support assembly includes a fan assembly having a plurality of fan blades, a power shaft extending between the fan assembly and an engine of the aircraft, and a housing assembly positioned around the power shaft. The housing assembly includes a convergent housing and a sealing shroud. The convergent housing includes a cap, a base, and a middle portion extending therebetween. The base defines a first diameter, and the cap defines a second diameter less than the first diameter. The sealing shroud is positioned between the convergent housing and the power shaft. A gap is defined between the sealing shroud and the power shaft.

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Rivalta di Torino, Italy

Davide Lercara