GAS TURBINE ENGINE HAVING A HYDRAULIC FAN BRAKE

    公开(公告)号:US20250027427A1

    公开(公告)日:2025-01-23

    申请号:US18416269

    申请日:2024-01-18

    Abstract: A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.

    GEARBOX ASSEMBLY LUBRICATION SYSTEM FOR A TURBINE ENGINE

    公开(公告)号:US20240426374A1

    公开(公告)日:2024-12-26

    申请号:US18481582

    申请日:2023-10-05

    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.

    METHODS AND APPARATUS TO DETERMINE ENGINE STATUS WITH PLENUM MEASUREMENTS

    公开(公告)号:US20240402048A1

    公开(公告)日:2024-12-05

    申请号:US18329156

    申请日:2023-06-05

    Abstract: Methods and apparatus to determine engine status with plenum measurements are disclosed. A disclosed example apparatus for use with a gas turbine engine having bleed offtakes includes at least one sensor on or within the gas turbine engine, the at least one sensor to measure at least one parameter corresponding to: a first plenum within a casing of the gas turbine engine, the first plenum positioned at or downstream of a volume at which flows from respective ones of the bleed offtakes are combined, and a second plenum within the casing, the second plenum positioned upstream of the first plenum, and an interface to communicatively couple the at least one sensor to a controller, the controller to determine a status of the bleed offtakes based on the at least one parameter.

    LOW-PRESSURE TURBINE
    55.
    发明公开

    公开(公告)号:US20240271542A1

    公开(公告)日:2024-08-15

    申请号:US18169328

    申请日:2023-02-15

    Abstract: A low-pressure (LP) turbine includes an LP shaft, one or more stages of LP turbine stator vanes and LP turbine rotor blades, and one or more interstage seals. The LP turbine rotor blades are coupled to, and rotate with, the LP shaft. The one or more interstage seals are disposed between the one or more stages. The one or more interstage seals each includes a seal disk that extends radially inward of the LP turbine stator vanes. Each seal disk includes an outer shell that supports one or more seal teeth, and the outer shell rotates as the LP shaft rotates.

    Midshaft rating for turbomachine engines

    公开(公告)号:US11808214B2

    公开(公告)日:2023-11-07

    申请号:US18058034

    申请日:2022-11-22

    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.

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