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    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    412.
    发明申请
    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 审中-公开
    燃气涡轮发动机压缩机装置

    公开(公告)号：US20140157752A1

    公开(公告)日：2014-06-12

    申请号：US14179827

    申请日：2014-02-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC: F02K3/06

    CPC classification number: F02K3/06 ,  F02C3/107 ,  F05D2260/4031

    Abstract: A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. The pressure ratio across the first compressor is greater than or equal to about 7.

    Abstract translation: 一种设计燃气涡轮发动机的方法包括：提供包括风扇的风扇部分; 通过齿轮装置驱动风扇部分; 提供包括第一压缩机和第二压缩机的压缩机部分; 并且经由涡轮机部分驱动压缩机部分和齿轮装置。 跨越第一压缩机的压力比大于或等于约7。

    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    416.
    发明申请
    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 有权
    气体涡轮发动机轴承轴承配置

    公开(公告)号：US20130192199A1

    公开(公告)日：2013-08-01

    申请号：US13762970

    申请日：2013-02-08

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu

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

    CPC classification number: F01D25/16 ,  F01D25/162 ,  F02C7/06 ,  F02C7/36 ,  F02K3/04 ,  F05D2250/19 ,  F05D2260/40311

    Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.

    Abstract translation: 燃气涡轮发动机包括具有入口壳体和中间壳体的芯壳体，其分别提供入口壳体流动路径和中间壳体流动路径。 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压缩机部分。 轴包括主轴和具有波纹管的挠性轴。 柔性轴在第一端处固定到主轴，并且包括与第一端相对的第二端。 齿轮架构耦合到轴，并且风扇耦合到由齿轮架构旋转地驱动。 齿轮架构包括在第二端支撑的太阳齿轮。 第一轴承相对于中间壳体支撑轴，第二轴承相对于入口壳体支撑轴。 第二轴承从柔性轴径向向外设置。

    Accessory gearbox for gas turbine engine with variable transmission
    418.
    发明授权
    Accessory gearbox for gas turbine engine with variable transmission 有权

    公开(公告)号：US11346427B2

    公开(公告)日：2022-05-31

    申请号：US16274332

    申请日：2019-02-13

    Applicant: United Technologies Corporation

    Inventor： Hung Duong ,  Marc J. Muldoon ,  Gabriel L. Suciu

    IPC: F16H3/00 ,  F02C7/32 ,  F02K3/06 ,  F16H3/02

    Abstract: An auxiliary gearbox has a low speed input shaft driving a first plurality of accessories. A high speed input shaft drives a second plurality of accessories. The first plurality of accessories rotating about a first set of rotational axes, which are parallel to each other and perpendicular to a first plane. The second plurality of accessories rotating about a second set of rotational axes, which are parallel to each other and perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis of the high speed input shaft and the low speed input shaft. The low speed input shaft drives a variable speed transmission. A gas turbine engine is also disclosed.

    MULTI CORE GEARED GAS TURBINE ENGINE
    419.
    发明申请
    MULTI CORE GEARED GAS TURBINE ENGINE 有权

    公开(公告)号：US20210207530A1

    公开(公告)日：2021-07-08

    申请号：US16733504

    申请日：2020-01-03

    Applicant: United Technologies Corporation

    Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

    IPC: F02C6/20

    Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

    Intercooled cooling air with auxiliary compressor control
    420.
    发明授权
    Intercooled cooling air with auxiliary compressor control 有权

    公开(公告)号：US11002195B2

    公开(公告)日：2021-05-11

    申请号：US16374995

    申请日：2019-04-04

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Michael G. McCaffrey

    IPC: F02C9/18 ,  F02C7/143 ,  F02C7/32 ,  F02C7/18 ,  F01D17/10 ,  F01D25/12 ,  F02C7/36 ,  F04D29/28

    Abstract: A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

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