公开(公告)号：US20190276138A1

公开(公告)日：2019-09-12

申请号：US16293771

申请日：2019-03-06

Applicant: GE AVIO S.R.L

Inventor： Andrea Donnini ,  Davide Lercara ,  Alessandro Bordoni

IPC: B64C11/04 ,  F01D5/02 ,  F01D11/00 ,  B64D35/00

Abstract: 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.

公开(公告)号：US11306812B2

公开(公告)日：2022-04-19

申请号：US16585041

申请日：2019-09-27

Applicant: GE Avio S.r.l.

Inventor： Miriam Manzoni ,  Davide Lercara ,  Andrea Piazza

IPC: F16H57/04 ,  B64C27/12

Abstract: 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.

公开(公告)号：US11155334B2

公开(公告)日：2021-10-26

申请号：US16293771

申请日：2019-03-06

Applicant: GE AVIO S.R.L

Inventor： Andrea Donnini ,  Davide Lercara ,  Alessandro Bordoni

IPC: B64C11/02 ,  B64C11/04 ,  B64D35/00 ,  F01D5/02 ,  F01D11/00 ,  B64C27/32

Abstract: 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.