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    HORIZONTAL ENGINE BUILD STAND
    21.
    发明申请
    HORIZONTAL ENGINE BUILD STAND 审中-公开

    公开(公告)号：US20190153900A1

    公开(公告)日：2019-05-23

    申请号：US16250287

    申请日：2019-01-17

    Applicant: United Technologies Corporation

    Inventor： Gabrielle Murphy ,  Robert M. Lewis ,  Gregory E. Reinhardt

    IPC: F01D25/28 ,  B64F5/50 ,  B25H1/00 ,  F04D29/52 ,  F01D25/24 ,  F01D25/16 ,  F02C7/20

    Abstract: A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, said puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module.

    SEALS FOR GAS TURBINE ENGINE NACELLE COWLINGS
    26.
    发明申请
    SEALS FOR GAS TURBINE ENGINE NACELLE COWLINGS 有权
    气体涡轮发动机油封的密封

    公开(公告)号：US20170002746A1

    公开(公告)日：2017-01-05

    申请号：US14788135

    申请日：2015-06-30

    Applicant: United Technologies Corporation

    Inventor： Nigel D. Sawyers-Abbott ,  Gregory E. Reinhardt

    IPC: F02C7/28 ,  F02C7/12

    CPC classification number: F02C7/28 ,  F01D11/02 ,  F01D25/24 ,  F02C7/12 ,  F02C7/18 ,  F02C7/20 ,  F02C7/25 ,  F05D2220/32 ,  F05D2240/55

    Abstract: A gas turbine engine includes an engine core and core nacelle cowling coupled to the engine core. The engine core has a core member that extends radially outward from the engine core. The core nacelle cowling has a cowling member that extends radially inward towards the engine core. The cowling member is offset axially from the core member to form a labyrinth seal that bounds a coolant inlet, thereby fluidly coupling the fan duct flow of the gas turbine engine with a core compartment defined between the engine core and core nacelle cowling.

    Abstract translation: 燃气涡轮发动机包括联接到发动机芯的发动机芯和核心机罩罩。 发动机芯具有从发动机芯径向向外延伸的芯构件。 核心机罩罩具有朝向发动机芯径向向内延伸的整流罩构件。 整流罩构件与芯构件轴向偏移以形成界定冷却剂入口的迷宫式密封件，从而将燃气涡轮发动机的风扇管道流动与限定在发动机核心和核心机舱罩之间的核心隔室流体耦合。

    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    29.
    发明申请
    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 审中-公开
    气体涡轮发动机轴承轴承配置

    公开(公告)号：US20140230403A1

    公开(公告)日：2014-08-21

    申请号：US14012576

    申请日：2013-08-28

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Todd A. Davis ,  Gregory E. Reinhardt ,  Enzo DiBenedetto

    IPC: F01D25/16 ,  F02K3/06 ,  F02C7/36

    CPC classification number: F01D25/162 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/04 ,  Y02T50/671

    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.

    Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 第一轴支撑轴向设置在入口壳体流动路径和中间壳体流动路径之间的低压压缩机部分。 第一轴承相对于入口壳体支撑第一轴。 第二轴承相对于中间壳体支撑第二轴。 低压压缩机毂安装在第一轴上。 低压压缩机毂在第一轴承和第二轴承之间延伸到低压压缩机部分。

    Bearing compartment oil auto-ignition mitigation
    30.
    发明授权
    Bearing compartment oil auto-ignition mitigation 有权

    公开(公告)号：US10767560B2

    公开(公告)日：2020-09-08

    申请号：US16127365

    申请日：2018-09-11

    Applicant: United Technologies Corporation

    Inventor： Daniel S. Rogers ,  Taryn Narrow ,  Gregory E. Reinhardt ,  Collin P. Fitzgerald ,  Christopher M. Valva ,  Leonard Kolshak

    IPC: F02C7/06

    Abstract: A bearing assembly for a gas turbine engine includes, among other things, a bearing housing extending along an axis to define a bearing compartment, a lubricant seal assembly adjacent to the bearing housing to bound the bearing compartment, an air seal assembly defining a vent cavity along the bearing housing, wherein a mixing cavity is defined between the lubricant seal assembly and the air seal assembly, and wherein the bearing housing defines an airflow supply passage, an airflow vent passage and a scupper passage having respective fluid ports at different circumferential positions relative to the axis, the fluid port of the airflow vent passage fluidly coupled to the vent cavity, and the fluid ports of the airflow supply and scupper passages fluidly coupled to the mixing cavity. A method of sealing for a gas turbine engine is also disclosed.

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