公开(公告)号：US10605333B2

公开(公告)日：2020-03-31

申请号：US16035734

申请日：2018-07-16

Applicant: GE Avio S.r.l.

Inventor： Michele Gravina

IPC: F16H1/46 ,  F16H1/28 ,  F16D3/78

Abstract: A transmission device to divide torque between gears. The device comprising a coaxial motion input member and transmission members and comprising shafts having gears at an axial end. Flanges which project radially outwards from the shafts, at the opposite axial end with respect to the gears, are axially facing and arranged abutting against each other, and are fixed to the motion input member to divide the torque transmitted by the motion input member between the flanges. The second shaft being axially hollow. The first shaft comprising a first intermediate portion having an outside diameter smaller than the inside diameter of the second shaft and housed at least with radial clearance in the second shaft. The flanges comprise respective portions configured to deform under the action of forces acting between the motion input member and the gears to enable a fluctuation of the shafts with respect to an axis.

公开(公告)号：US10415693B2

公开(公告)日：2019-09-17

申请号：US15384179

申请日：2016-12-19

Applicant: GE Avio S.r.l.

Inventor： Paolo Altamura

IPC: F16H57/04 ,  F01D25/18 ,  F02C7/36 ,  F02K3/02 ,  F16C3/02 ,  B64C11/38 ,  F16H1/28

Abstract: An oil transfer assembly supplies oil into a moving, rotating tube extending along an axis. The assembly is provided with a support plate transversal to the axis and a sleeve, which is angularly fixed with respect to the support plate, it is configured to be coupled in a sliding and watertight way to a terminal section of the inlet of said tube and has at least one chamber for transferring oil into said terminal section of the inlet. The assembly is also equipped with at least two tubular bodies, which project axially from the support plate, define between them an annular channel communicating with the chamber and join the sleeve to the support plate in a watertight manner and with clearances so as to leave freedom of orientation of the sleeve around any direction orthogonal to the axis.

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：US20190194793A1

公开(公告)日：2019-06-27

申请号：US16210078

申请日：2018-12-05

Applicant: GE AVIO S.R.L.

Inventor： Lorenzo Rigo ,  Andrea Piazza ,  Diana Di Gioia

IPC: C23C8/38 ,  C23C8/02

CPC classification number: C23C8/38 ,  C21D1/06 ,  C21D9/32 ,  C22C38/44 ,  C22C38/52 ,  C23C8/02 ,  C23C8/34

Abstract: Methods for treating steel, along with the resulting treated steel, are provided. The method may comprise: nitriding a carburized Ferrium steel component such that the Ferrium steel component has a surface portion with a nitrogen content that is greater than 0% to about 5% by weight. Nitriding the Ferrium steel component may increase the surface hardness of the Ferrium steel. The surface portion may have a nitrogen content of about 0.05% to about 0.5% by weight.

公开(公告)号：US20190024755A1

公开(公告)日：2019-01-24

申请号：US16020064

申请日：2018-06-27

Applicant: GE Avio S.r.l.

Inventor： Michele GRAVINA ,  Marco FACCHINI

IPC: F16H1/46 ,  F16H57/08 ,  B23P15/14

Abstract: A transmission device for splitting torque between two coaxial gears, in particular for a planetary gearing for aeronautic applications, has a motion input member and two transmission members, which are coaxial and have respective shafts provided with gears at an axial end and respective external flanges, at the opposite axial end; the two flanges are axially facing and placed abutting against each other, and are fixed to the motion input member so as to split the torque transmitted from the motion input member between the two flanges; one of the two shafts is axially hollow and houses, with radial clearance, an intermediate portion of the other shaft; the latter is formed by at least two pieces which are coaxial and fixed to each other.

公开(公告)号：US20180355740A1

公开(公告)日：2018-12-13

申请号：US15997421

申请日：2018-06-04

Applicant: GE Avio S.r.l.

Inventor： Matteo Renato Usseglio ,  Enrico Ganzitti

IPC: F01D11/00 ,  F01D11/08 ,  F16J15/32

CPC classification number: F01D9/042 ,  F01D11/005 ,  F01D25/246 ,  F05D2240/15 ,  F05D2240/57

Abstract: An apparatus for turbine engine including a turbine section with at least one turbine stage having a stationary vane assembly and a rotating blade assembly with combustion gases flowing through the turbine stage in a fore to aft direction. An interface is formed between a portion of the outer casing and a portion of the stationary vane assembly defining a leak flow path (LFP) where a seal is placed to retard combustion gases in the leak path.

公开(公告)号：US20180265207A1

公开(公告)日：2018-09-20

申请号：US15891406

申请日：2018-02-08

Applicant: GE Avio S.r.l

Inventor： Cristian LAI

IPC: B64D31/00 ,  B64C11/30

CPC classification number: B64D31/00 ,  B64C11/303 ,  G05B19/042 ,  G05B2219/23328 ,  G06F9/5061

Abstract: One example aspect of the present disclosure is directed to a method for implementing modularized logic. The method includes accessing, by one or more processors, control software implemented on a controller to control operation of an aircraft engine. The method includes accessing, by the one or more processors, at least one of a plurality of propeller configuration parameters. The method includes modifying, by the one or more processors, the accessed at least one of the propeller configuration parameters independently of the control software.

公开(公告)号：US20170307061A1

公开(公告)日：2017-10-26

申请号：US15492040

申请日：2017-04-20

Applicant: GE Avio S.r.l.

Inventor： Michele GRAVINA ,  Federico DELLAVALLE ,  Elio PERONA

IPC: F16H57/04 ,  F16H1/28 ,  F16H57/08 ,  F01D15/12 ,  F01D25/18

CPC classification number: F16H57/0424 ,  F01D15/12 ,  F01D25/18 ,  F02C7/06 ,  F02C7/36 ,  F05D2260/40311 ,  F16H1/28 ,  F16H57/0427 ,  F16H57/043 ,  F16H57/0479 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/082

Abstract: An oil transfer unit has a rotating part, a stationary part provided with an oil mouth, and a floating part having a support body coupled to the stationary part; the floating part has an annular pad, that is distinct from the body and is provided with a cylindrical surface fitted onto an outer cylindrical surface of the rotating part in a non-contact configuration, with an annular groove provided between the pad and the rotating part to put the oil mouth into communication with an inner chamber of the rotating part; both sides of the groove are sealed by a hydrostatic seal between the cylindrical surfaces; an angular retaining constraint is provided to retain angularly the pad with respect to the body; at least one element is breakable or plastically deformable to release the angular constraint when the torque transferred to the body, in use, exceeds a defined threshold.

公开(公告)号：US09790810B2

公开(公告)日：2017-10-17

申请号：US14407918

申请日：2013-06-14

Applicant: GE AVIO S.R.L

Inventor： Daniele Coutandin ,  Stefano Zecchi

IPC: F01D25/12 ,  F01D11/24 ,  F02C7/18 ,  F01D25/14

CPC classification number: F01D25/12 ,  F01D11/24 ,  F01D25/145 ,  F02C7/18 ,  F05D2220/32 ,  F05D2250/712 ,  F05D2260/201 ,  F05D2260/231 ,  Y02T50/672 ,  Y02T50/676

Abstract: In a gas turbine for aeronautic engines, a stator body delimited by an outer lateral surface is cooled by an air cooling device having a plurality of circumferential tubes for distributing air on the outer lateral surface; each circumferential tube having a plurality of outlets for guiding respective cooling airflows towards the outer lateral surface and into a respective circumferential channel obtained between two groups of circumferential channels adjacent to each other and lapped by the flow of air leaving the circumferential channel.

公开(公告)号：US20170184309A1

公开(公告)日：2017-06-29

申请号：US15392749

申请日：2016-12-28

Applicant: GE AVIO S.r.l.

Inventor： Fabio TURRINI ,  Antonio PESCHIULLI ,  Marco MOTTA

IPC: F23R3/28 ,  F23R3/10 ,  F02C7/22

CPC classification number: F23R3/286 ,  F02C7/222 ,  F05D2220/32 ,  F05D2240/35 ,  F23D2900/11101 ,  F23R3/10

Abstract: An injection assembly for a combustor of a gas turbine has an outer body provided with inlet passages for comburent air, a conical tubular portion housed inside the outer body and delimiting partly an inner duct and an outer annular duct; a first and a second supply means for supplying a liquid fuel into the inner duct and, respectively, into the outer annular duct; at least one circumferential annular seat formed being carried by one of the tubular portion and the outer body, so as to collect a mass of liquid fuel advancing in the outer annular duct and make uniform the flow of liquid flowing out of the circumferential annular seat.