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    GEARBOX ASSEMBLY WITH LUBRICANT EXTRACTION VOLUME RATIO
    32.
    发明申请
    GEARBOX ASSEMBLY WITH LUBRICANT EXTRACTION VOLUME RATIO 有权

    公开(公告)号：US20250122836A1

    公开(公告)日：2025-04-17

    申请号：US18990706

    申请日：2024-12-20

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

    Inventor： Bugra H. Ertas ,  Xiaohua Zhang ,  Miriam Manzoni ,  Flavia Turi ,  Andrea Piazza ,  Arthur W. Sibbach ,  Brandon W. Miller

    IPC: F02C7/06 ,  F01D25/20 ,  F02C7/14 ,  F02C7/36 ,  F16H57/02 ,  F16H57/04

    Abstract: A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by V G V G ⁢ B . VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes a combustion section and the gearbox assembly. A fuel delivery system includes a fuel supply line for delivering fuel to the combustion section. A lubrication system includes a lubricant supply line for delivering lubricant to the gearbox assembly. A thermal management system includes a fuel-lubricant heat exchanger for cooling the lubricant with the fuel. The thermal management system selectively directs the fuel through fuel bypass lines or the lubricant through lubricant bypass lines to bypass the fuel-lubricant heat exchanger based on a fuel temperature or a lubricant temperature.

    Gearbox assembly lubrication system for a turbine engine
    33.
    发明授权
    Gearbox assembly lubrication system for a turbine engine 有权

    公开(公告)号：US12276333B2

    公开(公告)日：2025-04-15

    申请号：US18481582

    申请日：2023-10-05

    Applicant: General Electric Company

    Inventor： Brandon W. Miller ,  Arthur W. Sibbach ,  Andrew Hudecki ,  Ryan T. Roehm

    IPC: F01D25/18 ,  F02C7/36 ,  F16H57/04

    Abstract: A lubrication system for a gearbox assembly for a turbine engine. The gearbox assembly includes a gear assembly including one or more gears and one or more bearings. The lubrication system includes a sump. The sump is a primary reservoir that has a first lubricant level. The lubrication system also includes a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level that is greater than the first lubricant level. A plurality of drain ports includes a first drain port and a second drain port. The lubrication system fills the secondary reservoir with lubricant between the first lubricant level and the second lubricant level and a portion of the lubricant drains though the second drain port. The one or more gears collects the lubricant to supply the lubricant from the secondary reservoir to the one or more gears or to the one or more bearings.

    GEARBOX ASSEMBLY WITH LUBRICANT EXTRACTION VOLUME RATIO
    34.
    发明申请
    GEARBOX ASSEMBLY WITH LUBRICANT EXTRACTION VOLUME RATIO 有权

    公开(公告)号：US20250102058A1

    公开(公告)日：2025-03-27

    申请号：US18972185

    申请日：2024-12-06

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

    Inventor： Bugra H. Ertas ,  Xiaohua Zhang ,  Miriam Manzoni ,  Flavia Turi ,  Andrea Piazza ,  Arthur W. Sibbach ,  Brandon W. Miller

    IPC: F16H57/04 ,  F01D15/12 ,  F01D25/20

    Abstract: A gearbox assembly includes a gearbox having a gear assembly and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by V G V GB . VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a sump that is a primary reservoir having a first lubricant level and a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level. The lubrication system fills the secondary reservoir with a lubricant between the first lubricant level and the second lubricant level. The gear assembly collects the lubricant in the secondary reservoir to supply the lubricant to the gear assembly.

    TURBINE ENGINE INCLUDING A STEAM SYSTEM
    36.
    发明申请
    TURBINE ENGINE INCLUDING A STEAM SYSTEM 有权

    公开(公告)号：US20250052175A1

    公开(公告)日：2025-02-13

    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.

    LUBRICATION SYSTEM FOR A TURBINE ENGINE
    37.
    发明申请
    LUBRICATION SYSTEM FOR A TURBINE ENGINE 有权

    公开(公告)号：US20250043697A1

    公开(公告)日：2025-02-06

    申请号：US18537490

    申请日：2023-12-12

    Applicant: General Electric Company

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

    IPC: F01D25/20 ,  F02C7/06

    Abstract: A lubrication system for a turbine engine having a longitudinal centerline axis and one or more rotating components. The lubrication system includes a primary lubrication system that supplies lubricant to the one or more rotating components during normal operation of the turbine engine. The lubrication system also includes an auxiliary lubrication system. The auxiliary lubrication system includes an auxiliary reservoir and a lubricant dispersion device. The auxiliary reservoir stores the lubricant therein. The lubricant dispersion device rotates about the longitudinal centerline axis. The lubricant dispersion device collects the lubricant in the auxiliary reservoir and disperses the lubricant to the one or more rotating components as the lubricant dispersion device rotates.

    UNIDIRECTIONAL FAN BRAKE FOR A GAS TURBINE ENGINE
    38.
    发明申请
    UNIDIRECTIONAL FAN BRAKE FOR A GAS TURBINE ENGINE 有权

    公开(公告)号：US20240426250A1

    公开(公告)日：2024-12-26

    申请号：US18488420

    申请日：2023-10-17

    Applicant: General Electric Company

    Inventor： Eric Barre ,  Brandon W. Miller ,  Arthur W. Sibbach

    IPC: F02C7/36

    Abstract: A turbine engine has a longitudinal centerline axis. The turbine engine includes a fan, a turbo-engine, and a unidirectional brake. The fan includes a plurality of fan blades that rotate in a first direction about the longitudinal centerline axis. The turbo-engine includes a combustor that combusts compressed air and fuel to generate combustion gases and a low-pressure turbine including a low-pressure shaft. The low-pressure turbine receives the combustion gases to rotate the low-pressure turbine. The fan is coupled to the low-pressure shaft such that rotation of the low-pressure shaft causes the fan to rotate in the first direction. A unidirectional brake is coupled to the low-pressure shaft to prevent rotation of the low-pressure shaft and, thus, the fan in a second direction opposite the first direction.

    Turbine engine with fan bypass water injection to augment thrust
    39.
    发明授权
    Turbine engine with fan bypass water injection to augment thrust 有权

    公开(公告)号：US12173669B1

    公开(公告)日：2024-12-24

    申请号：US18452203

    申请日：2023-08-18

    Applicant: General Electric Company

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

    IPC: F02K3/02 ,  F02K3/06

    Abstract: A gas turbine has a core turbine engine, and a fan having a plurality of fan blades. A nacelle surrounds the fan and at least a portion of the core turbine engine. The nacelle defines an inlet arranged upstream of the fan, and a bypass flow passage downstream of the fan defined between the nacelle and the core turbine engine. The gas turbine also includes a bypass flow passage water injection system that includes (a) at least one water injection nozzle assembly arranged to inject water into at least one of the inlet of the nacelle, or into the bypass flow passage, and (b) a water injection supply system arranged to supply water from a storage tank to the at least one water injection nozzle assembly. Water is provided by the bypass flow passage water injection system during a high power operating states of the gas turbine to augment thrust.

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