公开(公告)号：US11873767B2

公开(公告)日：2024-01-16

申请号：US17508545

申请日：2021-10-22

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

Inventor： Andrea Piazza ,  Darek Zatorski ,  Juraj Hrubec ,  David M. Ostdiek

IPC: F02C7/36 ,  F01D1/24

CPC classification number: F02C7/36 ,  F01D1/24 ,  F05D2220/36 ,  F05D2260/40311

Abstract: A gear assembly for use with a turbomachine 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 gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

公开(公告)号：US20230399983A1

公开(公告)日：2023-12-14

申请号：US17806574

申请日：2022-06-13

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

Inventor： Ravindra Shankar Ganiger ,  Andrea Piazza ,  Gontla Nagashiresha ,  Bugra H. Ertas ,  Sanjeev Jha

IPC: F02C7/36 ,  F01D15/10 ,  F02K3/06

CPC classification number: F02C7/36 ,  F01D15/10 ,  F02K3/06 ,  F05D2220/768 ,  F05D2260/40311

Abstract: A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

公开(公告)号：US11713721B1

公开(公告)日：2023-08-01

申请号：US17929542

申请日：2022-09-02

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

Inventor： Andrea Piazza ,  Jeffrey D. Clements

IPC: F02C7/36 ,  F02C3/067 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02C3/067 ,  F02K3/06 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2200/221 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine 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 a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox 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 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.

公开(公告)号：US20230212987A1

公开(公告)日：2023-07-06

申请号：US18058034

申请日：2022-11-22

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

Inventor： Narayanan Payyoor ,  Weize Kang ,  Brandon W. Miller ,  Bugra Ertas ,  Andrea Piazza

IPC: F02C7/36 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/60 ,  F05D2260/40

Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)½ and three hundred (ft/sec)½. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.

公开(公告)号：US20220364636A1

公开(公告)日：2022-11-17

申请号：US17488784

申请日：2021-09-29

Applicant: GE Avio S.r.l.

Inventor： Lucia Azzini ,  Fabio De Bellis ,  Andrea Piazza

IPC: F16H55/06 ,  F16H1/28 ,  F16H57/08 ,  F02C7/36 ,  C23C16/50 ,  C23C16/26 ,  C23C16/30 ,  C23C16/34 ,  C23C24/04

Abstract: A component includes a metallic substrate having a tribological surface and a coating. The coating includes a first layer disposed on the tribological surface and a second layer disposed on the first layer. The first layer includes titanium, chromium, or a diamond-like carbon (DLC). The second layer includes a disulfide.

公开(公告)号：US20220325669A1

公开(公告)日：2022-10-13

申请号：US17581057

申请日：2022-01-21

Applicant: GE Avio S.r.l.

Inventor： Andrea Piazza

IPC: F02C7/36 ,  F02C7/06

Abstract: A gear assembly comprises a plurality of planet gear layshafts that have an outer surface having a plurality of gear surfaces and a surface having one or more bearing surfaces. The one or more bearing surfaces of the surfaces of the planet gear layshafts have a first case hardening depth and a first nitriding hardness depth. The gear surfaces of the outer surface of the planet gear layshafts have a second case hardening depth.

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：US12253155B2

公开(公告)日：2025-03-18

申请号：US18661105

申请日：2024-05-10

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

Inventor： Andrea Piazza ,  Ravindra Shankar Ganiger

IPC: F16H55/08 ,  F16H57/02

Abstract: A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.

公开(公告)号：US20250035206A1

公开(公告)日：2025-01-30

申请号：US18910919

申请日：2024-10-09

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

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

IPC: F16H57/025 ,  F16H57/02 ,  F16H57/023

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. The gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.

公开(公告)号：US12085026B2

公开(公告)日：2024-09-10

申请号：US18604985

申请日：2024-03-14

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

Inventor： Andrea Piazza ,  Jeffrey D. Clements

IPC: F02C7/36 ,  F02C3/067 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02C3/067 ,  F02K3/06 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2200/221 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine 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 a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox 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 2.0-4.0.