公开(公告)号：US20230112829A1

公开(公告)日：2023-04-13

申请号：US18080849

申请日：2022-12-14

Applicant: GE Avio S.r.l.

Inventor： Matteo Renato Usseglio ,  Antonio Giuseppe D'Ettole ,  Andrea Depalma

IPC: F01D5/20 ,  F01D5/32 ,  F01D5/22 ,  F01D5/06 ,  F01D5/02

Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.

公开(公告)号：US20220162961A1

公开(公告)日：2022-05-26

申请号：US17471621

申请日：2021-09-10

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

Inventor： Roberto Maddaleno ,  Antonio Giuseppe D'Ettole ,  Matteo Renato Usseglio ,  Alessandra Torri ,  Darek Tomasz Zatorski

IPC: F01D21/02 ,  F01D21/00

Abstract: A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.

公开(公告)号：US20220128010A1

公开(公告)日：2022-04-28

申请号：US17469960

申请日：2021-09-09

Applicant: GE Avio S.r.l.

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

IPC: F02C7/36 ,  F02C7/06 ,  F01D25/24

Abstract: A method for engine assembly is provided, the method including forming an interdigitated rotor assembly comprising an inner rotor assembly rotatable at a first speed different from an outer rotor assembly rotatable at a second speed; fastening a gear assembly to the interdigitated rotor assembly to form an interdigitated turbine assembly; and coupling the interdigitated turbine assembly to a gas generator, wherein coupling the interdigitated turbine assembly to the gas generator includes coupling a planet carrier assembly of the gear assembly to a static frame of the gas generator.

公开(公告)号：US20210277832A1

公开(公告)日：2021-09-09

申请号：US17178371

申请日：2021-02-18

Applicant: GE Avio S.r.l.

Inventor： Roberto Maddaleno ,  Matteo Renato Usseglio ,  Darek Tomasz Zatorski

IPC: F02C7/36 ,  F01D25/16

Abstract: Turbomachines and turbine sections of a turbomachine are provided. For example, a turbomachine comprises a turbine section having a turbine comprising a first plurality and a second plurality of turbine rotor blades, which are alternatingly spaced along an axial direction. At least one turbine blade of the first plurality of turbine blades is attached to a first support member assembly and at least one turbine blade of the second plurality of turbine blades is attached to a second support member assembly. The turbomachine further comprises a spool that connects the turbine with one or more components outside the turbine section, a first rotational support, and a gearbox. Both the first support member assembly and the second support member assembly are attached to the first rotational support and coupled to the gearbox such that the first and second pluralities of turbine rotor blades are rotatable with one another through the gearbox.

公开(公告)号：US20210108522A1

公开(公告)日：2021-04-15

申请号：US16987747

申请日：2020-08-07

Applicant: GE Avio S.r.l.

Inventor： Andrea Depalma ,  Antonio Giuseppe D'Ettole ,  Matteo Renato Usseglio

IPC: F01D5/30 ,  F01D5/02

Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. Each of the first plurality of blades includes a blade root portion secured to the rotatable annular outer drum rotor. Each of the blade root portions includes one or more structural radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum and one or more axial retention features for axially retaining each of the blade root portions within the rotatable annular outer drum.

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：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：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.