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    Epicyclic gear train
    11.
    发明授权
    Epicyclic gear train 有权

    公开(公告)号：US10890245B2

    公开(公告)日：2021-01-12

    申请号：US16805917

    申请日：2020-03-02

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

    IPC: F16H57/04 ,  F02C7/36 ,  F02K3/06

    Abstract: A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).

    Planetary gear system arrangement with auxiliary oil system
    12.
    发明授权
    Planetary gear system arrangement with auxiliary oil system 有权

    公开(公告)号：US10648383B2

    公开(公告)日：2020-05-12

    申请号：US15621406

    申请日：2017-06-13

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  William G. Sheridan ,  Lawrence E. Portlock

    IPC: F01D25/16 ,  F01N3/20 ,  F01D25/18 ,  F02C3/10 ,  F02K3/06 ,  F02C7/36 ,  F02C7/06 ,  F02C7/10 ,  F01N11/00 ,  F16N7/34

    Abstract: A method of designing a gas turbine engine includes configuring a speed reduction device for driving a fan and configuring a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with the first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing is configured to also include a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.

    Gas turbine engine with geared architecture
    13.
    发明授权
    Gas turbine engine with geared architecture 有权

    公开(公告)号：US10570855B2

    公开(公告)日：2020-02-25

    申请号：US16166235

    申请日：2018-10-22

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

    IPC: F16H57/04 ,  F02K3/06 ,  F02C7/36

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbo fan shaft and a turbo fan supported on the fan shaft, a compressor section having compressor hubs with blades driven about an axis, and an epicyclic gear system driving the fan shaft. The gear system includes a carrier supporting intermediate gears that mesh with a sun gear, a ring gear surrounding and meshing with the intermediate gears, the ring gear including first and second portions each having an inner periphery with teeth, the first and second portions abutting one another at a radial interface, each of the first and second portions including a flange extending radially outward, and the first and second portions having grooves at the radial interface which form a hole that expels oil through the ring gear to a gutter, and an input shaft driving the fan shaft through the gear system, the input shaft connected to the sun gear.

    Ring gear mounting arrangement with oil scavenge scheme
    18.
    发明授权
    Ring gear mounting arrangement with oil scavenge scheme 有权
    环形齿轮安装与清油方案

    公开(公告)号：US09115650B2

    公开(公告)日：2015-08-25

    申请号：US14293279

    申请日：2014-06-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Lawrence E. Portlock

    IPC: F16H57/021 ,  F02C7/36 ,  F16H57/04 ,  F01D5/02 ,  F16H57/08

    CPC classification number: F16H57/0424 ,  F01D5/027 ,  F01D25/18 ,  F02C7/28 ,  F02C7/36 ,  F05D2240/55 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F05D2260/98 ,  F16D1/076 ,  F16H1/28 ,  F16H57/0402 ,  F16H57/042 ,  F16H57/0421 ,  F16H57/043 ,  F16H57/0458 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/08 ,  Y10T29/49462

    Abstract: A turbine engine includes a fan section including a plurality of fan blades, a turbine section, and an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine section and the fan section. The epicyclic gear train includes a plurality of intermediate gears. A carrier supports the plurality of intermediate gears. A sun gear meshes with the plurality of intermediate gears and a ring gear surrounding and meshing with the plurality of intermediate gears. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from the axis. An epicyclic gear train for a turbine engine and method of designing an epicyclic gear train are also disclosed.

    Abstract translation: 涡轮发动机包括风扇部分，其包括多个风扇叶片，涡轮部分和联接在涡轮部分和风扇部分之间的行星齿轮系，用于在涡轮部分和风扇部分之间提供减速。 行星齿轮系包括多个中间齿轮。 载体支撑多个中间齿轮。 太阳齿轮与多个中间齿轮啮合，并且环形齿轮围绕并与多个中间齿轮啮合。 齿圈包括第一和第二部分，每个部分具有带齿的内周边。 所述环形齿轮的第一和第二部分具有与所述齿相对的外周表面，所述外周表面提供第一厚度，第二厚度大于所述第一厚度并且从所述第一厚度轴向向内，以及凸缘，其径向延伸远离所述轴线。 还公开了一种用于涡轮发动机的行星齿轮系和设计行星齿轮系的方法。

    Ring gear mounting arrangement with oil scavenge scheme
    19.
    发明授权
    Ring gear mounting arrangement with oil scavenge scheme 有权

    公开(公告)号：US10830334B2

    公开(公告)日：2020-11-10

    申请号：US16819322

    申请日：2020-03-16

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Lawrence E. Portlock

    IPC: F16H57/04 ,  F16H57/08 ,  F01D5/02 ,  F02C7/36 ,  F16D1/076 ,  F01D25/18 ,  F02C7/28 ,  F16H1/28

    Abstract: An epicyclic gear train for a gas turbine engine according to an example of the present disclosure includes, among other things, a gutter having an annular channel, a sun gear rotatable about an axis, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear arranged about and intermeshing with the intermediary gears, the ring gear having an aperture axially aligned with the annular channel. The ring gear includes axially spaced apart walls that extend radially outward to define a passageway, and the passageway is arranged radially between the aperture and the annular channel such that the walls inhibit an axial flow of an oil passing from the aperture toward the annular channel.

    EPICYCLIC GEAR TRAIN
    20.
    发明申请
    EPICYCLIC GEAR TRAIN 审中-公开

    公开(公告)号：US20200347744A1

    公开(公告)日：2020-11-05

    申请号：US16805917

    申请日：2020-03-02

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

    IPC: F01D15/12 ,  F01D25/18 ,  F01D25/16 ,  F01D1/02 ,  F01D5/02 ,  F02C7/32

    Abstract: A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).

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