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    TURBINE SECTION SUPPORT FOR A GAS TURBINE ENGINE
    134.
    发明申请
    TURBINE SECTION SUPPORT FOR A GAS TURBINE ENGINE 审中-公开
    涡轮机部分支持燃气涡轮发动机

    公开(公告)号：US20160195019A1

    公开(公告)日：2016-07-07

    申请号：US14797253

    申请日：2015-07-13

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F02C7/20 ,  F02C7/06 ,  F02C3/04

    CPC classification number: F02C7/20 ,  F01D25/16 ,  F01D25/162 ,  F02C3/04 ,  F02C7/06 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2240/50 ,  F05D2240/54 ,  F05D2240/60 ,  F05D2250/36 ,  F16C19/55 ,  F16C35/06

    Abstract: A gas turbine engine includes a compressor portion, a combustor fluidly connected to the compressor portion via a primary flowpath, and a turbine portion fluidly connected to the combustor via the primary flowpath. The turbine section includes a first turbine portion and a second turbine portion. The second turbine portion is at a low pressure relative to the first turbine portion. A first turbine shaft is supported relative to a second turbine shaft by a first bearing, the first bearing having an inner diameter and an outer diameter, with the inner diameter of the first bearing being connected to one of the first shaft and the second shaft and the outer diameter of the first bearing being connected to the other of the first shaft and the second shaft.

    Abstract translation: 燃气涡轮发动机包括压缩机部分，经由主流路与流体连接到压缩机部分的燃烧器以及通过主流路与燃烧器流体连接的涡轮机部分。 涡轮机部分包括第一涡轮机部分和第二涡轮机部分。 第二涡轮机部分相对于第一涡轮部分处于低压。 第一涡轮轴通过第一轴承相对于第二涡轮轴支撑，第一轴承具有内径和外径，第一轴承的内径连接到第一轴和第二轴中的一个， 第一轴承的外径与第一轴和第二轴的另一个连接。

    FAN DRIVE GEAR SYSTEM
    135.
    发明申请
    FAN DRIVE GEAR SYSTEM 审中-公开
    风扇驱动齿轮系统

    公开(公告)号：US20160084105A1

    公开(公告)日：2016-03-24

    申请号：US14950326

    申请日：2015-11-24

    Applicant: United Technologies Corporation

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

    IPC: F01D15/12

    CPC classification number: F02C7/36 ,  F01D25/16 ,  F05D2260/40311 ,  F05D2260/98

    Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted aft of the speed change mechanism.

    Abstract translation: 燃气涡轮发动机包括风扇部和用于驱动风扇部的变速机构。 第一风扇部支承轴承安装在变速机构的前方，第二风扇部轴承安装在变速机构的后方。

    AUXILIARY DEVICE FOR THREE AIR FLOW PATH GAS TURBINE ENGINE
    136.
    发明申请
    AUXILIARY DEVICE FOR THREE AIR FLOW PATH GAS TURBINE ENGINE 审中-公开
    三级空气流量气体涡轮发动机辅助装置

    公开(公告)号：US20150267551A1

    公开(公告)日：2015-09-24

    申请号：US14458619

    申请日：2014-08-13

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F01D15/08 ,  F01D1/18

    CPC classification number: F02K3/075 ,  F02C3/13 ,  F02C7/36 ,  F02C9/18 ,  F02K3/00 ,  F02K3/02 ,  F02K3/077 ,  F02K3/10

    Abstract: A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.

    Abstract translation: 燃气涡轮发动机具有包括至少一个级的风扇转子，所述至少一个级将空气的一部分输送到低压管道中，另一部分空气进入压缩机。 压缩机由涡轮转子驱动，风扇转子由风扇驱动涡轮驱动。 通道选择性地将来自低压管道的空气穿过增压压缩机。

    GAS TURBINE ENGINE SYSTEMS AND RELATED METHODS INVOLVING MULTIPLE GAS TURBINE CORES
    137.
    发明申请
    GAS TURBINE ENGINE SYSTEMS AND RELATED METHODS INVOLVING MULTIPLE GAS TURBINE CORES 有权
    气体涡轮发动机系统及涉及多个气体涡轮机的相关方法

    公开(公告)号：US20130298565A1

    公开(公告)日：2013-11-14

    申请号：US13680857

    申请日：2012-11-19

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F02C9/00

    CPC classification number: F02C9/00 ,  F02C3/113 ,  F02K3/06 ,  F02K3/12 ,  F05D2220/76 ,  F05D2240/40 ,  F05D2260/74

    Abstract: Gas turbine engine systems and related methods involving multiple gas turbine cores are provided. In this regard, a representative gas turbine engine includes: an inlet; a blade assembly mounted to receive intake air via the inlet; and multiple gas turbine cores located downstream of the blade assembly, each of the multiple gas turbine cores being independently operative in a first state, in which rotational energy is provided to rotate the blade assembly, and a second state, in which rotational energy is not provided to rotate the blade assembly.

    Abstract translation: 提供了涉及多个燃气涡轮机磁芯的燃气涡轮发动机系统和相关方法。 在这方面，代表性的燃气涡轮发动机包括：入口; 安装成经由所述入口接收进气的叶片组件; 以及位于叶片组件下游的多个燃气涡轮机芯，多个燃气涡轮机芯中的每一个独立地在第一状态下工作，其中提供旋转能量以旋转叶片组件，以及第二状态，其中转动能不是 被提供以旋转叶片组件。

    Multi-wall deposited thin sheet structure
    138.
    发明授权
    Multi-wall deposited thin sheet structure 有权

    公开(公告)号：US11441227B2

    公开(公告)日：2022-09-13

    申请号：US16706083

    申请日：2019-12-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William J. Brindley ,  Gary D. Roberge

    IPC: C23C24/04 ,  C23C24/08 ,  F01D5/28 ,  B05D1/02 ,  F01D5/14 ,  F01D5/18 ,  B05D1/36

    Abstract: A method for forming a metallic structure having multiple layers includes providing a main tool having a main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing the first layer of material on the main formation surface using a cold-spray deposition technique. The method also includes positioning a secondary tool having a secondary formation surface in a portion of a first volume defined by a first surface of the first layer of material. The method also includes depositing a second layer of material on the secondary formation surface using the cold-spray deposition technique. The method also includes removing the secondary tool such that the first volume is positioned between the first layer of material and the second layer of material.

    Multi-disk bladed rotor assembly for rotational equipment
    139.
    发明授权
    Multi-disk bladed rotor assembly for rotational equipment 有权

    公开(公告)号：US11371351B2

    公开(公告)日：2022-06-28

    申请号：US16796241

    申请日：2020-02-20

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F01D5/06 ,  F01D5/30

    Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The disk mounts connect the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount. The first disk mount is integral with the first rotor disk. The first disk mount projects axially through the second rotor disk.

    Power takeoff transmission
    140.
    发明授权
    Power takeoff transmission 有权

    公开(公告)号：US11333076B2

    公开(公告)日：2022-05-17

    申请号：US15851089

    申请日：2017-12-21

    Applicant: United Technologies Corporation

    Inventor： Gary D. Roberge

    IPC: F02C7/32 ,  F02C7/36

    Abstract: A power takeoff and gearbox system of a multi-spool gas turbine engine includes a high rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, a first gearbox operably connected to the high rotor towershaft, a low rotor towershaft operably connected to and driven by a second spool of the gas turbine engine, and a second gearbox operably connected to the low rotor towershaft. The high rotor towershaft is located at a first case of the gas turbine engine and the low rotor towershaft is located at a second case of the gas turbine engine axially forward of the first case.

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