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    LOW WEIGHT LARGE FAN GAS TURBINE ENGINE
    81.
    发明申请
    LOW WEIGHT LARGE FAN GAS TURBINE ENGINE 审中-公开
    低重量级风机涡轮发动机

    公开(公告)号：US20150252752A1

    公开(公告)日：2015-09-10

    申请号：US14428049

    申请日：2013-02-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu

    IPC: F02K3/06 ,  F02C7/20 ,  F02C3/107

    CPC classification number: F02K3/04 ,  F01D17/105 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06 ,  F04D29/325 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2260/4031

    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.

    Abstract translation: 一种燃气涡轮发动机包括具有可围绕轴线旋转的多个风扇叶片的风扇，压缩机部分，与压缩机部分流体连通的燃烧器以及与燃烧器流体连通的涡轮部分。 风扇限定风扇直径，涡轮部分包括直径小于0.50的风扇驱动涡轮，风扇直径的大小。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。

    LPC flowpath shape with gas turbine engine shaft bearing configuration
    83.
    发明授权
    LPC flowpath shape with gas turbine engine shaft bearing configuration 有权
    LPC流路形状与燃气轮机轴承轴承配置

    公开(公告)号：US09038366B2

    公开(公告)日：2015-05-26

    申请号：US14067354

    申请日：2013-10-30

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

    IPC: F02K3/02 ,  F02C1/06 ,  F02C3/13 ,  F01D25/16 ,  F02K3/04 ,  F02C7/36 ,  F02C9/18 ,  F01D5/14

    CPC classification number: F02C3/13 ,  F01D5/143 ,  F01D25/162 ,  F02C7/36 ,  F02C9/18 ,  F02K3/04 ,  Y02T50/673

    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 flowpath. 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 in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. 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路的入口壳体和中间壳体。 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。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 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。

    ATR FULL RING SLIDING NACELLE
    84.
    发明申请
    ATR FULL RING SLIDING NACELLE 有权
    ATR全滑动滑轨

    公开(公告)号：US20150125284A1

    公开(公告)日：2015-05-07

    申请号：US14187021

    申请日：2014-02-21

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F01D25/24

    CPC classification number: B64D29/06 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/128 ,  F05D2240/1281 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2240/91 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/34 ,  F05D2250/75 ,  F05D2260/96 ,  Y10T29/49721

    Abstract: A gas turbine engine includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion, and a fore bi-fi. The rail is coupled to the fore pylon portion and extending in the aft direction from the stationary portion. The second annular portion is arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion comprises an aft bi-fi configured to engage with the fore bi-fi when the gas turbine engine is in the closed position.

    Abstract translation: 燃气涡轮发动机包括铁芯，第一环形部分，轨道和第二环形部分。 第一环形部分是静止的并且适于部分地围绕发动机芯。 第一环形部分包括前挂架连接部分和前部双向翼片。 导轨连接到前挂架部分并且在后方向上从固定部分延伸。 第二环形部分布置在第一部分的后部并且联接到轨道。 第二环形部分可沿着发动机芯心中心线在关闭位置和至少一个打开位置之间移动。 第二环形部分包括后部双层结构，其构造成当燃气涡轮发动机处于关闭位置时与前部双向接合。

    GAS TURBINE ENGINE VARIABLE PITCH FAN BLADE
    85.
    发明申请
    GAS TURBINE ENGINE VARIABLE PITCH FAN BLADE 审中-公开
    气体涡轮发动机变量风扇叶片

    公开(公告)号：US20150125259A1

    公开(公告)日：2015-05-07

    申请号：US14187612

    申请日：2014-02-24

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Brian D. Merry

    IPC: F01D7/02 ,  F02C7/36

    CPC classification number: F02C7/36 ,  F02K3/06 ,  Y02T50/671

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括除了别的以外的风扇部分，其包括可围绕发动机轴线旋转的风扇，其中多个风扇叶片围绕风扇叶片轴线可旋转。 齿轮架构与风扇通信，并由涡轮机部分驱动。 风扇以第一速度旋转，并且涡轮部分以不同于第一速度的第二速度旋转，并且与风扇部分连通的固定区域风扇喷嘴。

    TANDEM THRUST REVERSER WITH MULTI-POINT ACTUATION
    86.
    发明申请
    TANDEM THRUST REVERSER WITH MULTI-POINT ACTUATION 有权
    TANDEM THRUST REVERSER多点执行

    公开(公告)号：US20150122912A1

    公开(公告)日：2015-05-07

    申请号：US14184398

    申请日：2014-02-19

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02K1/76 ,  F02K1/72 ,  B23P19/04

    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 comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator.

    Abstract translation: 一个实施例包括枢轴推力反向器，其包括第一串联枢轴门子组件，其包括连接的内板和外板。 包括第二串联枢轴门子组件，包括连接的内板和外板。 还包括位于附接位置的第一侧上以枢转第一串联枢转门子组件的第一致动器，位于附接位置的第二侧以枢转第二串联枢转门子组件的第二致动器，以及位于 基本上径向地相对于所述附接位置枢转所述第一串联枢轴门子组件和所述第二串联枢轴门子组件。 第一串联枢转门构造成从收起枢转以由第一致动器和第三致动器展开，并且第二串联枢转门构造成从收起枢转以由第二致动器和第三致动器展开。

    CONJOINED REVERSE CORE FLOW ENGINE ARRANGEMENT
    87.
    发明申请
    CONJOINED REVERSE CORE FLOW ENGINE ARRANGEMENT 有权
    连续反向核心流量发动机装置

    公开(公告)号：US20150121838A1

    公开(公告)日：2015-05-07

    申请号：US14190175

    申请日：2014-02-26

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Brian D. Merry

    IPC: F02C6/02 ,  B64D29/06 ,  F02K1/54

    CPC classification number: B64D29/06 ,  B64D27/20 ,  F01D13/003 ,  F02K1/52 ,  F02K1/54 ,  F02K1/60 ,  F02K1/64 ,  F05D2250/314

    Abstract: A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.

    Abstract translation: 联合燃气涡轮发动机的系统具有第一发动机，第一发动机具有第一推进器和第二发动机，第一发动机具有第一轴线，第一发动机机芯具有第二轴线，第二发动机具有带有第三轴线的第二推进器和具有第四轴线的第二发动机机芯 。 第一轴和第三轴彼此平行; 并且第二轴线和第四轴线彼此成角度。

    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    89.
    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：US20140186158A1

    公开(公告)日：2014-07-03

    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: F02C3/107 ,  F02C7/36

    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。

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