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    PIVOT THRUST REVERSER WITH MULTI-POINT ACTUATION
    291.
    发明申请
    PIVOT THRUST REVERSER WITH MULTI-POINT ACTUATION 有权
    PIVOT扭矩反转器具有多点执行

    公开(公告)号：US20150008268A1

    公开(公告)日：2015-01-08

    申请号：US14184376

    申请日：2014-02-19

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02K1/62 ,  B64D29/00

    CPC classification number: F02K1/763 ,  B23P19/04 ,  B64D29/00 ,  B64D33/04 ,  F02K1/60 ,  F02K1/605 ,  F02K1/62 ,  F02K1/64 ,  F02K1/72 ,  F05D2260/50 ,  Y10T29/49229

    Abstract: One embodiment includes a pivot thrust reverser with a first pivot door with an upper linkage and a lower linkage and a second pivot door, spaced from the first pivot door, with an upper linkage and a lower linkage. A first actuator is located on a first side of an attachment location to drive the first pivot door. A second actuator is located on a second side of the attachment location to drive the second pivot door. A third actuator is located substantially radially opposite the attachment location to drive both the first pivot door and the second pivot door. The first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator. The second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.

    Abstract translation: 一个实施例包括枢转推力反向器，其具有带有上连杆的第一枢转门和下连杆以及与第一枢转门隔开的第二枢转门，具有上连杆和下连杆。 第一致动器位于附接位置的第一侧以驱动第一枢轴门。 第二致动器位于附接位置的第二侧以驱动第二枢转门。 第三致动器基本上位于与附接位置径向相对的位置，以驱动第一枢转门和第二枢转门。 第一枢转门构造成通过第一致动器和第三致动器由收起位置枢转到展开位置。 第二枢转门构造成通过第二致动器和第三致动器由收起位置枢转到展开位置。

    Gas turbine engine shaft bearing configuration
    293.
    发明授权
    Gas turbine engine shaft bearing configuration 有权
    燃气轮机轴承配置

    公开(公告)号：US08863491B2

    公开(公告)日：2014-10-21

    申请号：US14012773

    申请日：2013-08-28

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Karl L. Hasel

    IPC: F02C1/06 ,  F02K3/02

    CPC classification number: F02C7/06 ,  F01D25/162 ,  F02C3/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/00 ,  F02K3/04 ,  Y02T50/671 ,  Y10T29/4932

    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 geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.

    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。 入口箱内设有齿轮架构。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分轴向地布置在入口壳体流动路径和中间壳体流动路径之间。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。

    REVERSE FLOW GAS TURBINE ENGINE AIRFLOW BYPASS
    294.
    发明申请
    REVERSE FLOW GAS TURBINE ENGINE AIRFLOW BYPASS 有权
    反向气流涡轮发动机气流旁路

    公开(公告)号：US20140250862A1

    公开(公告)日：2014-09-11

    申请号：US14190144

    申请日：2014-02-26

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Brian D. Merry

    IPC: F02K3/06

    CPC classification number: F02K3/06 ,  F05D2210/40 ,  F05D2250/314 ,  Y02T50/671

    Abstract: A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.

    Abstract translation: 燃气涡轮发动机具有包括风扇和动力涡轮的推进器，通过过渡管道空气动力地连接到推进器的发动机核心，以及允许来自发动机芯的空气绕过动力涡轮机的过渡管道中的旁通阀。

    GAS TURBINE ENGINE SYSTEMS INVOLVING TIP FANS
    295.
    发明申请
    GAS TURBINE ENGINE SYSTEMS INVOLVING TIP FANS 审中-公开
    涉及风机的气体涡轮发动机系统

    公开(公告)号：US20140241856A1

    公开(公告)日：2014-08-28

    申请号：US13777723

    申请日：2013-02-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gary D. Roberge ,  Gabriel L. Suciu

    IPC: F02C3/067

    CPC classification number: F02C3/067 ,  F02C3/107 ,  F02K3/072 ,  F02K3/077 ,  F05D2260/40311

    Abstract: Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the second rotatable set of blades defining an inner fan and a tip fan and being located downstream of the first set of rotatable blades; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades.

    Abstract translation: 提供了涉及尖端风扇的燃气涡轮发动机系统。 在这方面，代表性的燃气涡轮发动机系统包括：多级风扇，具有第一可转动的叶片组和第二可反向旋转的叶片组，第二可旋转叶片限定内部风扇和顶端风扇， 位于第一组可旋转叶片的下游; 以及行星差速齿轮组件，其操作以接收扭矩输入并且差分地施加到第一组叶片和第二组叶片的扭矩输入。

    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    297.
    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。

    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE
    299.
    发明申请
    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE 有权
    基础系统架构

    公开(公告)号：US20140020404A1

    公开(公告)日：2014-01-23

    申请号：US14034720

    申请日：2013-09-24

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Michael E. McCune ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann ,  Jason Husband

    IPC: F02C7/06

    CPC classification number: F02C7/06 ,  F01D25/18 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  Y02T50/671

    Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.

    Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括能量消除等于输入到齿轮系统中的能量的小于约2％的能量。

    Low weight large fan gas turbine engine
    300.
    发明授权
    Low weight large fan gas turbine engine 有权

    公开(公告)号：US11585293B2

    公开(公告)日：2023-02-21

    申请号：US14428049

    申请日：2013-02-10

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu

    IPC: F02K3/04 ,  F01D17/10 ,  F04D29/32 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06

    Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The fan defines a fan diameter and the turbine section includes a fan drive turbine with a diameter less than 0.50 the size of the fan diameter. A geared architecture is driven by the turbine section for rotating the fan about the axis.

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