公开(公告)号：US11841141B2

公开(公告)日：2023-12-12

申请号：US17072465

申请日：2020-10-16

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

Inventor： Massimo Giovanni Giambra ,  Joseph Douglas Monty ,  Stephen John Howell

IPC: F23R3/54 ,  F23R3/06 ,  F02C3/14 ,  F02C7/18 ,  F23R3/46 ,  F01D9/02 ,  F23R3/50

CPC classification number: F23R3/54 ,  F02C3/145 ,  F02C7/18 ,  F23R3/06 ,  F23R3/46 ,  F01D9/023 ,  F05D2220/323 ,  F05D2240/35 ,  F23R3/50 ,  F23R2900/00017

Abstract: An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

公开(公告)号：US11835127B1

公开(公告)日：2023-12-05

申请号：US17816164

申请日：2022-07-29

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

Inventor： Leonardo Coviello ,  Bugra H. Ertas ,  Eric R. Westervelt ,  Andrea Piazza ,  Juraj Hrubec

IPC: F16H57/08 ,  F02C7/36 ,  F16H57/01

CPC classification number: F16H57/08 ,  F02C7/36 ,  F05D2260/40311 ,  F16H57/01 ,  F16H2057/085

Abstract: A gearbox assembly includes a gear assembly that includes a planet gear, a pin disposed within the planet gear, a first sensor, and a second sensor. The first sensor is disposed within the pin and is configured to produce a signal indicative of a strain of the pin. The second sensor is disposed within the pin and is configured to produce a signal indicative of a vibration of the pin. Another gearbox assembly includes a gear assembly including a planet gear, a pin disposed within the planet gear, and a strain sensor. The strain sensor is disposed within the pin and is configured to produce a signal indicative of a strain of the pin. The strain sensor is located within the pin at a circumferential location of the pin that is opposite to a location of a force acting on the pin when the planet gear rotates about the pin.

公开(公告)号：US20230340911A1

公开(公告)日：2023-10-26

申请号：US17929105

申请日：2022-09-01

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

Inventor： Bugra H. Ertas ,  Ravindra Shankar Ganiger ,  Andrea Piazza

IPC: F02C7/36 ,  F16H57/08 ,  F16H57/025

CPC classification number: F02C7/36 ,  F16H57/08 ,  F16H57/025

Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling.

公开(公告)号：US20230203993A1

公开(公告)日：2023-06-29

申请号：US18167751

申请日：2023-02-10

Applicant: GE Avio S.r.l.

Inventor： Pietro Molesini ,  Andrea Piazza ,  Fabio De Bellis

IPC: F02C7/36 ,  F01D25/18

CPC classification number: F02C7/36 ,  F01D25/18 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. 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：US11674400B2

公开(公告)日：2023-06-13

申请号：US17393743

申请日：2021-08-04

Applicant: GE Avio S.r.l. ,  Avio Polska Sp. z o.o.

Inventor： Matteo Renato Usseglio ,  Enrico Ganzitti ,  Gianfranco Brandino ,  Rafal Robak ,  Tomasz Mucha

IPC: F01D9/04 ,  F01D9/02 ,  F01D25/24 ,  F01D11/00

CPC classification number: F01D9/02 ,  F01D9/041 ,  F01D11/005 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/128

Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.

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.