公开(公告)号：US20230167745A1

公开(公告)日：2023-06-01

申请号：US17888539

申请日：2022-08-16

Applicant: GE Avio S.r.l

Inventor： Roberto Maddaleno ,  Matteo Renato Usseglio

IPC: F01D5/30

CPC classification number: F01D5/3053 ,  F01D5/3015 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/30

Abstract: A rotating blade assembly for a turbine engine having a drive shaft, the rotating blade assembly comprising a disc, at least one blade assembly, and a retainer. The disc being operably coupled to the drive shaft and including a seat having at least a portion of a first through hole. The at least one blade assembly having an upper platform, a lower platform, a dovetail extending from the lower platform, and a blade extending between the upper platform and the lower platform. The retainer assembly securing the disc to the at least one blade assembly and comprising a hollow tubular element, a pin, and a fastener.

公开(公告)号：US20230160341A1

公开(公告)日：2023-05-25

申请号：US17663536

申请日：2022-05-16

Applicant: GE Avio S.r.l.

Inventor： Fabio De Bellis ,  Leonardo Orlando ,  Cristiano Consales ,  Francesco Santacroce

IPC: F02C7/06 ,  B64D33/08 ,  F16H57/04 ,  F02C7/36

CPC classification number: F02C7/06 ,  B64D33/08 ,  F16H57/0471 ,  F16H57/0423 ,  F02C7/36

Abstract: An integrated lubrication system and an engine that includes the integrated lubrication system. The system has a first and a second lubrication supply line and one or more spray bars. The first lubrication supply line extends radially inward toward a central axis of the engine, has a first plurality of jet outlets, and is configured to deliver a lubrication fluid to a first location on one or more engine components. The second lubrication supply line extends parallel to the central axis, has a second plurality of jet outlets, and is configured to deliver the lubrication fluid to a second location on the one or more engine components. The first lubrication supply line is configured to lubricate the one or more engine components in a first engine power condition and the second lubrication supply line is configured to lubricate the one or more engine components in a second engine power condition.

公开(公告)号：US20230142715A1

公开(公告)日：2023-05-11

申请号：US17972498

申请日：2022-10-24

Applicant: GE Avio S.r.l.

Inventor： Juraj Hrubec ,  Leonardo Coviello

IPC: F02C7/36 ,  F16H57/08

CPC classification number: F02C7/36 ,  F16H57/082 ,  F05D2260/40311 ,  F05D2220/323

Abstract: A gear assembly for use with a turbomachine engine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly and is driven by the input shaft. A component of the gear assembly drives the output shaft. The planet gears can be compound planet gears having a first stage and a second stage.

公开(公告)号：US11603916B2

公开(公告)日：2023-03-14

申请号：US16691916

申请日：2019-11-22

Applicant: GE AVIO S.R.L.

Inventor： Andrea Piazza

IPC: F16H57/04 ,  F16N29/04 ,  G07C5/08 ,  F16H1/20 ,  F16H1/36 ,  F01M11/10 ,  F02C7/06 ,  F16C19/52 ,  G01M13/04

Abstract: Systems and methods of monitoring lubrication of a gear assembly during operation of a machine provide for receiving at a control system, a signal from a sensor indicative of a value obtained by the sensor for an electrical property of a circuit crossing the gear assembly operably coupled to the machine, ascertaining whether the value for the electrical property corresponds to a warning level for a condition of the lubricant film, and outputting a control command when the value for the electrical property corresponds to the warning level for the condition of the lubricant film.

公开(公告)号：US20230051515A1

公开(公告)日：2023-02-16

申请号：US17529556

申请日：2021-11-18

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Mehdi Milani Baladi ,  Randy M Vondrell

IPC: B64C17/06 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02 ,  B64C29/00

Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

公开(公告)号：US11555521B2

公开(公告)日：2023-01-17

申请号：US17074906

申请日：2020-10-20

Applicant: GE Avio S.r.l.

Inventor： Tomasz Kowalewski ,  Ivan Borra ,  Gian Mario Bragallini ,  Vincenzo Giordano

IPC: F16H1/14 ,  F16D1/108 ,  F02C7/32 ,  F16D1/08 ,  F16D1/10

Abstract: A gearbox comprising a main unit comprising a first casing and a first hollow shaft, and a secondary unit comprising a second casing and a second hollow shaft, and a drive shaft comprising a first clutch portion and a second clutch portion, which engage the first and second hollow shafts in an angularly fixed and axially sliding manner. The gearbox further including an axial retaining device comprising an axial shoulder supported in a fixed potion by an axial end on one of the first or second hollow shafts, and an external radial projection arranged in an intermediate position, and an external radial projection arranged in an intermediate position along the drive shaft between the first and second clutch portions.

公开(公告)号：US20220397040A1

公开(公告)日：2022-12-15

申请号：US17835879

申请日：2022-06-08

Applicant: GE Avio S.r.l.

Inventor： Pietro Molesini ,  Fabio De Bellis ,  Andrea Piazza

IPC: F01D25/18 ,  F16H57/04 ,  F16H1/28

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.

公开(公告)号：US11519346B2

公开(公告)日：2022-12-06

申请号：US16920159

申请日：2020-07-02

Applicant: GE Aviation Czech s.r.o. ,  GE Avio S.r.l.

Inventor： Giuseppe Cervelli ,  Simone Castellani ,  Miriam Manzoni ,  Giuseppe Bellocchio ,  Vojtech Jirasek

IPC: F02D29/02 ,  B64C11/38 ,  B64C11/40 ,  B63H3/10 ,  F02B61/04

Abstract: A variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.

公开(公告)号：US11473507B2

公开(公告)日：2022-10-18

申请号：US17364707

申请日：2021-06-30

Applicant: GE Avio S.r.l.

Inventor： Pietro Molesini ,  Andrea Piazza ,  Fabio De Bellis

IPC: F02C7/36 ,  F01D17/16 ,  F02C7/06 ,  F01D25/18

Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

公开(公告)号：US20220184641A1

公开(公告)日：2022-06-16

申请号：US17643544

申请日：2021-12-09

Applicant: GE Avio S.r.l.

Inventor： Saypen Baraggia Au Yeung ,  Pietro Molesini ,  Miriam Manzoni ,  Fabio De Bellis

IPC: B04C5/28 ,  B01D45/16 ,  B04C5/04 ,  F02C7/06

Abstract: An air/oil separator is provided. The air/oil separator includes an oil manifold having a first air/oil inlet and a second air/oil inlet; a first separation chamber in communication with the first air/oil inlet; and a second separation chamber separate from the first separation chamber, the second separation chamber in communication with the second air/oil inlet.