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    Turbine engine including a steam system
    11.
    发明授权
    Turbine engine including a steam system 有权

    公开(公告)号：US12221905B1

    公开(公告)日：2025-02-11

    申请号：US18366256

    申请日：2023-08-07

    Applicant: General Electric Company

    Inventor： Arthur W. Sibbach ,  Robert R. Rachedi ,  Brandon W. Miller ,  Jeffrey D. Rambo ,  Daniel A. Niergarth

    IPC: F01K21/04 ,  F01K7/16 ,  F02C6/00

    Abstract: A turbine engine for an aircraft. The turbine engine includes a fan, a combustor in a core air flowpath that generates combustion gases, a core shaft, a turbine that receives the combustion gases to rotate the turbine, and a steam system. The steam system extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath. The steam system includes one or more water storage devices that store the water therein. The one or more water storage devices include a first state in which the one or more water storage devices increase or maintain a level of the water as the water flows through the one or more water storage devices, and a second state in which the one or more water storage devices decrease the level of the water in the one or more water storage devices.

    METHOD OF OPERATING A LUBRICATION SYSTEM FOR A TURBINE ENGINE
    12.
    发明申请
    METHOD OF OPERATING A LUBRICATION SYSTEM FOR A TURBINE ENGINE 有权

    公开(公告)号：US20250035013A1

    公开(公告)日：2025-01-30

    申请号：US18537494

    申请日：2023-12-12

    Applicant: General Electric Company

    Inventor： Brandon W. Miller ,  Arthur W. Sibbach ,  Andrew Hudecki

    IPC: F01D25/20

    Abstract: A method of operating a lubrication system for a turbine engine having a fan and one or more rotating components. The lubrication system includes a primary lubrication system and an auxiliary lubrication system. The method includes supplying lubricant to the one or more rotating components from the primary lubrication system during a normal operation of the turbine engine, determining whether at least one of a fuel pressure is less than a fuel pressure threshold or a hydraulic pressure is less than a hydraulic pressure threshold, and activating the auxiliary lubrication system to supply the lubricant to the one or more rotating components from the auxiliary lubrication system when the fuel pressure is less than the fuel pressure threshold or the hydraulic pressure is less than the hydraulic pressure threshold.

    LUBRICATION SYSTEM FOR A TURBINE ENGINE
    13.
    发明申请
    LUBRICATION SYSTEM FOR A TURBINE ENGINE 有权

    公开(公告)号：US20250020070A1

    公开(公告)日：2025-01-16

    申请号：US18517878

    申请日：2023-11-22

    Applicant: General Electric Company

    Inventor： Arthur W. Sibbach ,  Brandon W. Miller ,  Andrew Hudecki ,  Randy M. Vondrell ,  Jeffrey D. Rambo

    IPC: F01D25/20 ,  F02C7/06

    Abstract: A lubrication system for a turbine engine. The turbine engine includes a fan having a fan shaft and one or more rotating components. The lubrication system includes one or more tanks that stores lubricant therein, a primary lubrication system, and an auxiliary lubrication system. The primary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump that is coupled to the fan shaft. The auxiliary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components based on a pressure of the lubricant in the primary lubrication system. Rotation of the fan shaft causes the auxiliary pump to pump the lubricant to the one or more rotating components.

    MIDSHAFT RATING FOR TURBOMACHINE ENGINES
    15.
    发明公开
    MIDSHAFT RATING FOR TURBOMACHINE ENGINES 审中-公开

    公开(公告)号：US20240117769A1

    公开(公告)日：2024-04-11

    申请号：US18481597

    申请日：2023-10-05

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

    Inventor： Narayanan Payyoor ,  Weize Kang ,  Brandon W. Miller ,  Bugra H. 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)1/2 and three hundred (ft/sec)1/2. 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.

    Turbofan blade blocking apparatus
    17.
    发明授权
    Turbofan blade blocking apparatus 有权

    公开(公告)号：US11788549B2

    公开(公告)日：2023-10-17

    申请号：US17493600

    申请日：2021-10-04

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas J. Kray ,  Brandon W. Miller ,  Egbert Geertsema

    IPC: F04D29/52 ,  F04D19/00

    CPC classification number: F04D29/522 ,  F04D19/002

    Abstract: Turbofan blade blocking apparatus are disclosed. An example turbofan engine includes a containment casing, a fan, at least one of a trench filler or an abradable layer at least partially aligned with the fan in an axial direction defined by the turbofan engine, at least one of the trench filler or the abradable layer fixed to an inner radial surface of the containment casing, and a metal blocker coupled to the containment casing forward of the fan, an aft end of the metal blocker interfacing with at least one of the trench filler or the abradable layer.

    MIDSHAFT RATING FOR TURBOMACHINE ENGINES
    18.
    发明公开
    MIDSHAFT RATING FOR TURBOMACHINE ENGINES 审中-公开

    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.

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