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    TURBOMACHINE FAN CLUTCH
    41.
    发明申请
    TURBOMACHINE FAN CLUTCH 审中-公开
    涡轮风扇离合器

    公开(公告)号：US20160003143A1

    公开(公告)日：2016-01-07

    申请号：US14769887

    申请日：2014-01-31

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William G. Sheridan ,  Michael E. McCune

    IPC: F02C3/107

    CPC classification number: F02C3/107 ,  F02C7/36 ,  F05D2260/4023 ,  F16D41/088 ,  F16D43/06

    Abstract: A gas turbine engine assembly includes, among other things, a clutch configured to move from a first position to a second position in response to rotation of a gas turbine engine fan at a speed greater than a threshold speed. Whether the clutch is in the first position or the second position, the clutch permits rotation of the gas turbine engine fan in a first direction. When the clutch is in the first position, the clutch limits rotation of the gas turbine engine fan only in an opposite, second direction. The clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure. The clutch is removable on-wing.

    Abstract translation: 燃气涡轮发动机组件尤其包括一个离合器，该离合器配置成响应于燃气涡轮发动机风扇以大于阈值速度的速度旋转而从第一位置移动到第二位置。 离合器是否处于第一位置或第二位置，离合器允许燃气涡轮发动机风扇沿第一方向旋转。 当离合器处于第一位置时，离合器仅在相反的第二方向限制燃气涡轮发动机风扇的旋转。 离合器设置在通过拆卸后部发动机盖结构可接近和可拆卸的隔室内。 离合器是可拆卸的机翼。

    Oil baffle for gas turbine fan drive gear system
    42.
    发明授权
    Oil baffle for gas turbine fan drive gear system 有权
    燃气轮机风扇驱动齿轮系统的油挡板

    公开(公告)号：US09194255B2

    公开(公告)日：2015-11-24

    申请号：US14173874

    申请日：2014-02-06

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Michael E. McCune

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

    CPC classification number: F01D25/18 ,  F02C7/36 ,  F05D2230/60 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0486 ,  Y02T50/671 ,  Y10T29/4932

    Abstract: A turbine engine comprises compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and intermediate gears. A method of designing a turbine engine is also disclosed.

    Abstract translation: 涡轮发动机包括压缩机和涡轮机部分。 行星齿轮系包括载体，太阳齿轮和围绕太阳齿轮啮合的中间齿轮。 中间齿轮由载体支撑。 挡板包括在太阳齿轮和中间齿轮中的至少一个附近的润滑通道，用于将润滑剂引导到太阳齿轮和中间齿轮中的至少一个上。 还公开了一种设计涡轮发动机的方法。

    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE
    43.
    发明申请
    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 审中-公开
    具有齿轮架构的气体涡轮发动机

    公开(公告)号：US20150300197A1

    公开(公告)日：2015-10-22

    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: F01D15/12

    CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/4031 ,  F05D2260/40311 ,  F16H57/0479 ,  F16H57/0486

    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).

    Abstract translation: 用于燃气涡轮发动机的齿轮架构包括风扇轴和支撑在风扇轴上的风扇，并且限定大于约六的旁路流量比。 一个框架支撑风扇轴。 齿轮系驱动风扇轴。 齿轮系统具有大于或等于约2.3的齿轮减速比。 扭矩框架至少部分地支撑齿轮系统。 一个输入端耦合到齿轮系统。 下游涡轮机联接以可旋转地驱动输入联接器。 下游涡轮限定大于约五（5）的压力比。

    OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM
    46.
    发明申请
    OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM 审中-公开
    用于气体涡轮风扇驱动齿轮系统的油桶

    公开(公告)号：US20140348635A1

    公开(公告)日：2014-11-27

    申请号：US14455539

    申请日：2014-08-08

    Applicant: United Technologies, Corporation

    Inventor： William G. Sheridan ,  Michael E. McCune

    IPC: F01D25/18 ,  F16H57/04

    CPC classification number: F16H57/0427 ,  F01D25/18 ,  F02C3/04 ,  F02C7/36 ,  F05D2230/60 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H57/0421 ,  F16H57/0423 ,  F16H57/046 ,  F16H57/0479 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/082 ,  Y10T29/49316 ,  Y10T29/4932 ,  Y10T29/49323 ,  Y10T29/49464

    Abstract: A turbine engine includes a housing supporting compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle is supported relative to the carrier and includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and the intermediate gears. A spray bar is external to the carrier and is in communication with the lubrication passage. The spray bar terminates near the sun gear for directing lubricant on the sun gear.

    Abstract translation: 涡轮发动机包括壳体支撑压缩机和涡轮部分。 行星齿轮系包括载体，太阳齿轮和围绕太阳齿轮啮合的中间齿轮。 中间齿轮由载体支撑。 挡板相对于载体支撑，并且包括在太阳齿轮和中间齿轮中的至少一个附近的润滑通道，用于将润滑剂引导到太阳齿轮和中间齿轮中的至少一个上。 喷杆在载体外部并与润滑通道连通。 喷雾杆在太阳齿轮附近终止，用于将润滑剂引导到太阳齿轮上。

    PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM
    47.
    发明申请
    PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM 审中-公开
    辅助油系统布置与辅助油系统

    公开(公告)号：US20140230452A1

    公开(公告)日：2014-08-21

    申请号：US14266888

    申请日：2014-05-01

    Applicant: United Technologies Corporation

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

    IPC: F02C7/36 ,  F01D25/16 ,  F01D25/18

    CPC classification number: F01N3/208 ,  F01D25/16 ,  F01D25/18 ,  F01N3/2066 ,  F01N11/00 ,  F01N2610/01 ,  F01N2610/02 ,  F01N2610/1406 ,  F01N2610/142 ,  F01N2610/148 ,  F01N2900/1814 ,  F02C3/10 ,  F02C7/06 ,  F02C7/10 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  F16N7/34 ,  Y02T10/24 ,  Y02T50/671 ,  Y10T29/4932 ,  Y10T137/0324 ,  Y10T137/7297

    Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and 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 said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has 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.

    Abstract translation: 在一个示例性实施例中，燃气涡轮发动机包括风扇，驱动风扇的减速装置和用于沿旋转间隙润滑部件的润滑系统。 润滑系统包括润滑油输入。 固定的第一轴承从润滑剂输入端接收润滑剂并且具有其中润滑剂流动的第一种族。 用于旋转的第二轴承在第一轴承内。 第二轴承具有与所述第一座圈对准的第一开口，使得润滑剂可以从第一座圈通过第一开口流入第一管道。 第一个轴承还有一个润滑剂流入的第二个赛道。 第二轴承具有与第二座圈对准的第二开口，使得润滑剂可以从第二座圈通过第二开口流入第二导管。 第一和第二导管将润滑剂输送到不同的位置。

    Method of assembly for gas turbine fan drive gear system
    48.
    发明授权
    Method of assembly for gas turbine fan drive gear system 有权
    燃气轮机风扇驱动齿轮系统组装方法

    公开(公告)号：US08763251B2

    公开(公告)日：2014-07-01

    申请号：US13975635

    申请日：2013-08-26

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  William G. Sheridan

    IPC: B21K1/30

    CPC classification number: F02C7/36 ,  F02C3/107 ,  F02C7/32 ,  F02K3/06 ,  F05D2230/60 ,  F05D2260/40311 ,  F16H1/28 ,  F16H57/023 ,  F16H57/0423 ,  F16H57/0456 ,  F16H57/0479 ,  F16H57/0486 ,  F16H57/082 ,  Y02T50/671 ,  Y10T29/49464

    Abstract: A method of mounting a gear train to a torque frame includes providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining mounts for interconnecting the walls. Spaced apart apertures are provided between the mounts at an outer circumference of the carrier. Gear pockets are provided between the walls and mounts extending to the apertures, and a central opening in at least one of the walls. A plurality of intermediate gears and a sun gear are inserted in the carrier. A first ring gear half is placed about the outer periphery of the intermediate gears, and attach a torque frame to the carrier.

    Abstract translation: 将齿轮系安装到扭矩框架的方法包括提供具有中心轴线的单一载体，所述中心轴线包括间隔开的壁，并且周向间隔开的连接结构限定用于互连壁的支座。 间隔开的孔被设置在载体的外周的安装件之间。 在墙壁和延伸到孔的安装件之间设置齿轮袋，以及在至少一个壁中的中心开口。 多个中间齿轮和太阳齿轮插入载体中。 第一环形齿轮一半围绕中间齿轮的外周放置，并且将转矩框架附接到载体上。

    Flexible Support Structure For A Geared Architecture Gas Turbine Engine
    49.
    发明申请
    Flexible Support Structure For A Geared Architecture Gas Turbine Engine 有权
    用于齿轮架构燃气轮机发动机的灵活支撑结构

    公开(公告)号：US20140140819A1

    公开(公告)日：2014-05-22

    申请号：US14164364

    申请日：2014-01-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F01D25/16

    CPC classification number: F01D25/164 ,  F01D15/12 ,  F01D25/34 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/53 ,  Y02T50/671 ,  Y10T29/49229

    Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines a flexible support lateral stiffness with respect to the support lateral stiffness. An input to the gear system defines an input lateral stiffness with respect to the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括风扇轴和支撑风扇轴的支撑件。 支撑件限定了支撑横向刚度。 齿轮系驱动风扇轴。 柔性支撑件至少部分地支撑齿轮系统，并且相对于支撑横向刚度限定柔性支撑横向刚度。 齿轮系统的输入限定了相对于支撑横向刚度的输入横向刚度。 还公开了一种设计燃气涡轮发动机的方法。

    Flexible Support Structure For A Geared Architecture Gas Turbine Engine
    50.
    发明申请
    Flexible Support Structure For A Geared Architecture Gas Turbine Engine 有权
    用于齿轮架构燃气轮机发动机的灵活支撑结构

    公开(公告)号：US20140133958A1

    公开(公告)日：2014-05-15

    申请号：US14160601

    申请日：2014-01-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F02C7/36

    CPC classification number: F02C7/36 ,  F01D25/164 ,  F05D2260/96 ,  Y02T50/671

    Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括风扇轴和支撑风扇轴的支撑件。 支撑件限定支撑横向和支撑横向刚度中的至少一个。 齿轮系驱动风扇轴。 柔性支撑件至少部分地支撑齿轮系统，并且相对于支撑横向和支撑横向刚度中的至少一个限定柔性支撑横向和柔性支撑横向刚度中的至少一个。 相对于支撑横向和支撑横向刚度中的至少一个，齿轮系统的输入限定了输入横向刚度和输入横向刚度中的至少一个。 还公开了一种设计燃气涡轮发动机的方法。

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