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    GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY
    21.
    发明公开
    GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY 审中-公开

    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.

    Dual-winding synchronous reluctance machine composed of an excitation winding and a separate power winding
    23.
    发明授权
    Dual-winding synchronous reluctance machine composed of an excitation winding and a separate power winding 有权

    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.

    Fastener cover for flanged joint
    24.
    发明授权
    Fastener cover for flanged joint 有权

    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.

    ADDITIVE MANUFACTURING SYSTEMS OR METHODS FOR COMPRESSION OF MATERIAL BASED ON DETECTED TEMPERATURE
    25.
    发明公开
    ADDITIVE MANUFACTURING SYSTEMS OR METHODS FOR COMPRESSION OF MATERIAL BASED ON DETECTED TEMPERATURE 审中-公开

    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.

    Gearbox assembly
    27.
    发明授权
    Gearbox assembly 有权

    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.

    GEARBOX EFFICIENCY RATING FOR TURBOMACHINE ENGINES
    29.
    发明公开
    GEARBOX EFFICIENCY RATING FOR TURBOMACHINE ENGINES 审中-公开

    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.

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