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    Geared gas turbine engine
    171.
    发明授权
    Geared gas turbine engine 审中-公开

    公开(公告)号：US10669947B2

    公开(公告)日：2020-06-02

    申请号：US15206434

    申请日：2016-07-11

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan

    IPC: F02C7/36 ,  F02K3/06 ,  F16H1/28

    Abstract: A gas turbine engine includes a fan section that includes a fan rotatable about an engine axis. A compressor section includes a low pressure compressor rotatable about the engine axis. A turbine section includes a fan drive turbine for driving the fan and the low pressure compressor. A speed reduction device connects the fan drive turbine to the fan and the low pressure compressor. The speed reduction device includes a sun gear driven by an inner shaft. A plurality of intermediate gears surround the sun gear. A carrier supports the plurality of intermediate gears for driving the low pressure compressor. A ring gear is located radially outward from the intermediate gears and includes a forward portion for driving a fan drive shaft and an aft portion.

    ROLLER BEARINGS FOR HIGH RATIO GEARED TURBOFAN ENGINE
    173.
    发明申请
    ROLLER BEARINGS FOR HIGH RATIO GEARED TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20200056498A1

    公开(公告)日：2020-02-20

    申请号：US16663498

    申请日：2019-10-25

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan

    IPC: F01D15/12 ,  F16H57/08 ,  F01D25/16 ,  F02K3/06

    Abstract: A gear system for a geared turbofan engine is disclosed. The gear system includes a sun gear driven by a low spool shaft. The sun gear defines a sun gear diameter. A rotating carrier drives a fan. The carrier defines an outer carrier diameter and an inner carrier diameter. A non-rotating ring gear is also included. The ring gear defines a ring gear diameter and the ring gear diameter is smaller than the outer carrier diameter. A set of planet gears are mounted on corresponding rolling element bearing assemblies. Each roller element bearing assembly is supported within the carrier within a space defined between the carrier outer diameter and the carrier inner diameter. Each of the sun gear, ring gear and planet gears are substantially centered along a gearbox centerline transverse to an engine longitudinal axis and the gear system provides a speed reduction ratio between an input to the sun gear and an output from the carrier between 3:1 and 5:1. A method of creating a gear system for a geared turbofan engine and a geared turbofan system are also disclosed.

    Turbofan engine bearing and gearbox arrangement
    174.
    发明授权
    Turbofan engine bearing and gearbox arrangement 有权

    公开(公告)号：US10563576B2

    公开(公告)日：2020-02-18

    申请号：US15828510

    申请日：2017-12-01

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Michael E. McCune

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

    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan delivering air into a bypass duct and into a core engine, a fan drive gear system having a gear carrier, and a fan shaft coupling the fan drive gear system to the fan. The core engine includes a low spool including a low pressure turbine and a low pressure shaft, and a high spool including a high pressure turbine, a compressor, and a high pressure shaft coupling the high pressure turbine to the compressor. A first bearing is forward of the fan drive gear system, and supporting said fan shaft and said fan drive gear system, and a second bearing is aft of the fan drive gear system, and supporting the fan drive gear system.

    TURBOFAN ENGINE FRONT SECTION
    175.
    发明申请
    TURBOFAN ENGINE FRONT SECTION 审中-公开

    公开(公告)号：US20200032715A1

    公开(公告)日：2020-01-30

    申请号：US16436569

    申请日：2019-06-10

    Applicant: United 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 and is between 219 and 328.

    Tangential drive for gas turbine engine accessories
    176.
    发明授权
    Tangential drive for gas turbine engine accessories 有权

    公开(公告)号：US10526976B2

    公开(公告)日：2020-01-07

    申请号：US15498764

    申请日：2017-04-27

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

    IPC: F02C7/36

    Abstract: A gas turbine engine comprises a high speed spool and a low speed spool. A low speed power takeoff is driven by the low speed spool and a high speed power takeoff is driven by the high speed spool. The low speed power takeoff drives a plurality of low speed driven accessories about low speed spool drive axes and the high speed power takeoff drives a plurality of high speed driven accessories about high speed spool drive axes. The low speed spool drive axes are generally tangential to an envelope defined about a center axis of the engine, and the high speed spool drive axes are generally tangential to an envelope defined about the center.

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