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    Gas turbine engine with geared architecture
    11.
    发明授权
    Gas turbine engine with geared architecture 有权

    公开(公告)号：US10527151B1

    公开(公告)日：2020-01-07

    申请号：US16122236

    申请日：2018-09-05

    Applicant: United Technologies Corporation

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

    IPC: F16H57/04

    Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. There is a gutter with an annular channel. A gear system is connected to the fan shaft. There is a plurality of planetary gears and a ring gear with an aperture that is axially aligned with the annular channel. The ring gear includes a first portion with a first set of opposed angled teeth separated by a trough from a second portion with a second set of opposed angled teeth. A torque frame at least partially supports the gear system. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1 and a low fan pressure ratio of less than 1.45 across the fan blade alone.

    Tangential drive for gas turbine engine accessories
    12.
    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.

    FLUID COLLECTION GUTTER FOR A GEARED TURBINE ENGINE
    14.
    发明申请
    FLUID COLLECTION GUTTER FOR A GEARED TURBINE ENGINE 审中-公开

    公开(公告)号：US20190271236A1

    公开(公告)日：2019-09-05

    申请号：US16409167

    申请日：2019-05-10

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune

    IPC: F01D25/18 ,  F02C3/107

    Abstract: A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter at least partially circumscribes the gear train, and includes an inner surface and a channel. The channel receives fluid directed out of the gear train. The channel extends radially into the gutter from the inner surface to a channel end, and circumferentially to a channel outlet. At least a portion of the channel has a cross-sectional channel geometry that tapers axially as the channel extends radially towards the channel end.

    FLUID COLLECTION GUTTER FOR A GEARED TURBINE ENGINE
    15.
    发明申请
    FLUID COLLECTION GUTTER FOR A GEARED TURBINE ENGINE 审中-公开

    公开(公告)号：US20190170004A1

    公开(公告)日：2019-06-06

    申请号：US16267986

    申请日：2019-02-05

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune

    IPC: F01D9/06 ,  F02C3/107 ,  F01D25/18

    Abstract: A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter includes an inner surface and a channel that receives fluid directed out of the gear train. The inner surface at least partially defines a bore in which the gear train is arranged. The channel extends radially into the gutter from the inner surface, and circumferentially to a channel outlet. The bore has a cross-sectional bore area, and the channel has a cross-sectional channel area that is substantially equal to or less than about two percent of the bore area.

    FAN DRIVE GEAR SYSTEM
    18.
    发明申请
    FAN DRIVE GEAR SYSTEM 审中-公开

    公开(公告)号：US20190072040A1

    公开(公告)日：2019-03-07

    申请号：US16180548

    申请日：2018-11-05

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge ,  Michael E. McCune ,  William G. Sheridan

    IPC: F02C7/36 ,  F01D25/16

    Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. The speed change mechanism is an epicyclic gear train. A torque frame surrounds the speed change mechanism and includes a plurality of fingers. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted on the bearing support aft of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

    Gas turbine engine with geared architecture
    19.
    发明授权
    Gas turbine engine with geared architecture 有权

    公开(公告)号：US10107231B2

    公开(公告)日：2018-10-23

    申请号：US14753048

    申请日：2015-06-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F16H57/08 ,  F02K3/06 ,  F02C7/36 ,  F16H57/04

    Abstract: A geared architecture for a gas turbine engine comprises a fan shaft and a fan supported on the fan shaft and defining a bypass flow ratio greater than about six. A frame supports the fan shaft. A gear system drives the fan shaft. The gear system has a gear reduction ratio of greater than or equal to about 2.3. A torque frame at least partially supports the gear system. An input is coupled to the gear system. A downstream turbine is coupled to rotatably drive the input coupling. The downstream turbine defines a pressure ratio that is greater than about five (5).

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