GEARBOX ASSEMBLY
    1.
    发明公开
    GEARBOX ASSEMBLY 审中-公开

    公开(公告)号:US20240295259A1

    公开(公告)日:2024-09-05

    申请号:US18661105

    申请日:2024-05-10

    CPC classification number: F16H55/088 F16H57/02 F16H2057/02039

    Abstract: A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.

    AIRCRAFT ENGINE
    3.
    发明公开
    AIRCRAFT ENGINE 审中-公开

    公开(公告)号:US20240263587A1

    公开(公告)日:2024-08-08

    申请号:US18384640

    申请日:2023-10-27

    Inventor: Mark SPRUCE

    CPC classification number: F02C7/36 F16H1/28 F16H2057/02039

    Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.

    AIRCRAFT ENGINE
    7.
    发明公开
    AIRCRAFT ENGINE 审中-公开

    公开(公告)号:US20230212986A1

    公开(公告)日:2023-07-06

    申请号:US17980230

    申请日:2022-11-03

    Inventor: Mark SPRUCE

    CPC classification number: F02C7/36 F16H1/28 F16H2057/02039

    Abstract: A gas turbine engine for an aircraft configured with an engine core that has a turbine, a compressor, and a core shaft connecting the turbine to the compressor. A fan located upstream of the engine core, that has a plurality of fan blades. A gearbox arranged to receive an input from the core shaft and to output to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The gearbox having an overall gear mesh stiffness, and wherein the overall gear mesh stiffness of the gearbox is greater than or equal to 1.05×109 N/m and less than or equal to 8.0×109 N/m.

    Hybrid Orbitless Gearbox
    8.
    发明申请

    公开(公告)号:US20170292589A1

    公开(公告)日:2017-10-12

    申请号:US15511214

    申请日:2015-09-08

    Applicant: Leo J. Stocco

    Inventor: Leo J. Stocco

    Abstract: A Hybrid Orbitless gearbox combines the high speed capabilities of an Orbitless first stage with the high ratio of a Coupled Orbitless second stage. The two stages share a common set of carriers and offset members for high compactness and simplicity. A Coupled Orbitless second stage may also function on its own. Its all-pinion design supports a variety of engaging members that include gears, chains, sprockets, belts, cables and pulleys, among others. Stepped engaging members further amplify the reduction ratio and variable pitch diameter engaging members provide an infinitely variable transmission ratio.

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