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    Method of assembly for gear system with rotating carrier
    31.
    发明授权
    Method of assembly for gear system with rotating carrier 有权

    公开(公告)号：US11536204B2

    公开(公告)日：2022-12-27

    申请号：US17532085

    申请日：2021-11-22

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： William G. Sheridan ,  Michael E. McCune

    IPC: F16H1/28 ,  F02C7/36 ,  F16H57/08 ,  F02C7/06 ,  F01D25/16 ,  F01D25/18 ,  F02K3/06 ,  F16H57/00

    Abstract: A method of assembling a gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier, positioning baffles between side walls of the carrier such that an end of each of the baffles abuts a respective mount of the carrier, inserting intermediate gears through a central opening of the carrier, and then moving the intermediate gears radially outwardly into respective gear pockets of the carrier, inserting a sun gear through the central opening, moving the intermediate gears radially inwardly to engage the sun gear, coupling a shaft to the carrier, including attaching a torque frame to the carrier such that the torque frame interconnects the carrier and the shaft, placing first and second ring gear halves of a ring gear onto an outer periphery of the intermediate gears, and fixedly attaching the ring gear to an engine static structure. A gear system is also disclosed.

    Flexible coupling for geared turbine engine
    32.
    发明授权
    Flexible coupling for geared turbine engine 有权

    公开(公告)号：US11536203B2

    公开(公告)日：2022-12-27

    申请号：US17480503

    申请日：2021-09-21

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： William G. Sheridan ,  John R. Otto

    IPC: F02C7/36 ,  F02C7/06 ,  F02C7/20

    Abstract: A gas turbine engine includes a fan, a fan shaft coupled with the fan and arranged along an engine central axis, and a frame supporting the fan shaft. The frame defines a lateral frame stiffness (LFS). A non-rotatable flexible coupling and a rotatable flexible coupling support an epicyclic gear system. The couplings are subject to a Motion II of cantilever beam free end motion with respect to the engine central axis. The non-rotatable and the rotatable flexible couplings each have a stiffness of a common stiffness type under a common type of motion. The common stiffness type is a Stiffness B and the common type of motion is the Motion II. The Stiffness B of the rotatable flexible coupling is greater than the stiffness B of the non-rotatable flexible coupling, and a ratio of LFS/Stiffness B of the non-rotatable flexible coupling is in a range of 10-40.

    GAS TURBINE ENGINE FRONT SECTION
    34.
    发明申请
    GAS TURBINE ENGINE FRONT SECTION 有权

    公开(公告)号：US20220074350A1

    公开(公告)日：2022-03-10

    申请号：US17527542

    申请日：2021-11-16

    Applicant: Raytheon Technologies Corporation

    Inventor： Frederick M. Schwarz ,  William G. Sheridan

    IPC: F02C7/36 ,  F02K3/06

    Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio.

    Auxiliary oil system for geared gas turbine engine
    36.
    发明授权
    Auxiliary oil system for geared gas turbine engine 有权

    公开(公告)号：US11203974B2

    公开(公告)日：2021-12-21

    申请号：US16663537

    申请日：2019-10-25

    Applicant: Raytheon Technologies Corporation

    Inventor： William G. Sheridan

    IPC: F02C7/06 ,  F01D25/20 ,  F02K3/06

    Abstract: A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil system operates to ensure that the gear reduction will be adequately supplied with lubricant for at least 30 seconds at power should the main oil supply system fail.

    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE
    37.
    发明申请
    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE 有权

    公开(公告)号：US20210381442A1

    公开(公告)日：2021-12-09

    申请号：US17408607

    申请日：2021-08-23

    Applicant: Raytheon Technologies Corporation

    Inventor： William G. Sheridan

    IPC: F02C7/36 ,  F02C7/06 ,  F01D25/18 ,  F02K3/06 ,  F02C3/107

    Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.

    OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM
    38.
    发明申请
    OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM 有权

    公开(公告)号：US20210341049A1

    公开(公告)日：2021-11-04

    申请号：US17365220

    申请日：2021-07-01

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： William G. Sheridan ,  Michael E. McCune

    IPC: F16H57/04 ,  F01D25/18 ,  F02C7/36 ,  F02C3/04

    Abstract: A method of assembling an epicyclic gear train includes positioning a carrier, the carrier being a unitary structure with side walls and mounts unitary with one another, inserting intermediate gears through a central opening of the carrier, moving each of the intermediate gears into intermediate gear pockets, inserting baffles into the carrier, inserting a sun gear through the central opening, and moving the intermediate gears to intermesh with the sun gear, and moving a ring gear into engagement with the intermediate gears.

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