公开(公告)号：US20240200497A1

公开(公告)日：2024-06-20

申请号：US18592194

申请日：2024-02-29

Applicant: General Electric Company ,  GE AVIO S.R.L.

Inventor： David Justin Brady ,  Mirko Gernone ,  Nathan E. Gibson

IPC: F02C7/224 ,  B64D37/32 ,  F02C3/22 ,  F02C3/30

CPC classification number: F02C7/224 ,  B64D37/32 ,  F02C3/22 ,  F02C3/30 ,  F05D2260/213 ,  F05D2260/607 ,  F05D2260/99

Abstract: Methods and apparatus to produce hydrogen gas turbine propulsion are disclosed. An example apparatus to produce propulsion in a gas turbine engine includes a fluid line to transport hydrogen from a hydrogen supply and an inert gas from an inert gas supply to a gas turbine combustor. The apparatus also includes at least one heat exchanger coupled to the fluid line to heat the inert gas and the hydrogen in the fluid line.

公开(公告)号：US20240191794A1

公开(公告)日：2024-06-13

申请号：US18450050

申请日：2023-08-15

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

Inventor： Leonardo Orlando ,  Juraj Hrubec

IPC: F16H57/08 ,  F16C19/38 ,  F16H1/28

CPC classification number: F16H57/08 ,  F16C19/38 ,  F16H1/28 ,  F16C2361/65 ,  F16H2057/085

Abstract: A gearbox assembly includes a plurality of planet gears. At least one planet gear of the plurality of planet gears includes a layshaft. The gearbox assembly includes one or more roller bearings disposed within the layshaft and includes a plurality of rolling elements. The gearbox assembly also includes a bearing radial envelope in a range of 1.2 to 4.325. The gearbox assembly can also include a layshaft axial envelope in a range of 3.8 to 12.5.

公开(公告)号：US12007011B2

公开(公告)日：2024-06-11

申请号：US18165590

申请日：2023-02-07

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

Inventor： Andrea Piazza ,  Ravindra Shankar Ganiger

IPC: F16H55/08 ,  F16H57/02

CPC classification number: F16H55/088 ,  F16H57/02 ,  F16H2057/02039

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：US11952948B2

公开(公告)日：2024-04-09

申请号：US17813453

申请日：2022-07-19

Applicant: GE Avio S.r.l.

Inventor： Juraj Hrubec ,  Davide Lauria

IPC: F02C7/36 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F05D2260/40311

Abstract: A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.

公开(公告)号：US11946388B2

公开(公告)日：2024-04-02

申请号：US17863470

申请日：2022-07-13

Applicant: GE Avio S.r.l.

Inventor： Antonio Giusseppe D'Ettole ,  Andrea Depalma ,  Roberto Maddaleno ,  Matteo Renato Usseglio

IPC: F01D5/22 ,  F01D11/12

CPC classification number: F01D5/225 ,  F01D11/125 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/55

Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.

公开(公告)号：US20240093644A1

公开(公告)日：2024-03-21

申请号：US17946499

申请日：2022-09-16

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

Inventor： Paul Hadley Vitt ,  Matteo Renato Usseglio ,  Brian Lewis Devendorf

IPC: F02C7/22 ,  F02C6/00 ,  F02K3/08

CPC classification number: F02C7/22 ,  F02C6/00 ,  F02K3/08

Abstract: An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.

公开(公告)号：US11920522B2

公开(公告)日：2024-03-05

申请号：US17882268

申请日：2022-08-05

Applicant: GE Avio S.r.l.

Inventor： Diego di Leo ,  Lorenzo Cipolla ,  Simone Recchia ,  Cristian Lai

IPC: F02M51/00 ,  F02C7/232 ,  F02C9/26 ,  F16K37/00 ,  G01R27/02 ,  B64D37/00

CPC classification number: F02C9/263 ,  F02C7/232 ,  F16K37/0041 ,  G01R27/02 ,  B64D37/00

Abstract: Based upon a measured first resistance, a first delta curve is selected. Based upon a measured second resistance, a second delta curve is selected. A first fuel valve position (FVP) is received from a first position sensor, and the first FVP is applied to the first delta curve to obtain a first offset. A second FVP is received from a second position sensor, and the second FVP is applied to the second delta curve to obtain a second offset. The first offset is applied to the first measured FVP to obtain the first compensated FVP and the second offset is applied to the second measured FVP to obtain the second compensated FVP. The first compensated FVP and the second compensated FVP are correlated to obtain a final compensated FVP, which is applied to a desired fuel valve position to obtain a final fuel valve position.

公开(公告)号：US11894737B2

公开(公告)日：2024-02-06

申请号：US16606006

申请日：2018-05-15

Applicant: GE Avio S.r.l.

Inventor： Davide Ronchetto

IPC: H02K19/26 ,  H02K3/28 ,  H02K11/042 ,  H02P27/06 ,  H02M7/00

CPC classification number: H02K19/26 ,  H02K3/28 ,  H02K11/042 ,  H02M7/00 ,  H02P27/06

Abstract: A rotating field machine (200) including a stator (140) and a rotor (150) are provided. In particular, a dual-winding rotating field machine (200) in which the stator (140) includes two separate windings can be provided. In one example implementation, the stator (140) can include an excitation winding (220) configured to control an excitation current and a power winding (230) configured to control power flow to an electrical system. The dual-winding rotating field machine (200) can further include a starting mode and a generating mode. During the starting mode, both the excitation winding (220) and the power winding (230) can be coupled to one or more switching power converters (170). During the generating mode, the power winding (230) can be coupled to a variable frequency bus and the power converter (170) can be used to manage excitation power only.

公开(公告)号：US11873725B2

公开(公告)日：2024-01-16

申请号：US17694956

申请日：2022-03-15

Applicant: GE Avio S.r.l.

Inventor： Roberto Maddaleno ,  Andrea Depalma ,  Antonio Giuseppe D'Ettole ,  Matteo Renato Usseglio ,  Christian Campanale

IPC: F01D25/24 ,  F01D25/30

CPC classification number: F01D25/243 ,  F01D25/30 ,  F05D2240/70 ,  F05D2260/31

Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.

公开(公告)号：US20240009929A1

公开(公告)日：2024-01-11

申请号：US18218672

申请日：2023-07-06

Applicant: GE Avio S.r.l.

Inventor： Edoardo Maria Peradotto

IPC: B29C64/393 ,  B29C64/209 ,  B29C64/218

CPC classification number: B29C64/393 ,  B29C64/209 ,  B29C64/218 ,  B33Y30/00

Abstract: An additive manufacturing system for forming a component including a compression rig including a compression head supporting a top compression device applying a compressive load onto a top surface of the component, a pair of temperature sensors positioned on opposite sides of the top compression device and detecting a temperature of the top surface of the component, and a pair of distance sensors positioned on opposite sides of the top compression device and detecting a distance to the top surface of the component, and a controller configured to adjust a position of the compression rig and a load applied by the top compression device based on at least one of the detected temperatures and distances.