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    GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
    23.
    发明申请
    GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE 审中-公开
    燃气涡轮发动机，低压低压涡轮

    公开(公告)号：US20150315977A1

    公开(公告)日：2015-11-05

    申请号：US14755366

    申请日：2015-06-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

    IPC: F02C9/20 ,  F01D25/24 ,  F02K3/06 ,  F02C7/36 ,  F02C9/18

    CPC classification number: F02K3/06 ,  B64D27/26 ,  B64D2027/266 ,  B64D2027/268 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2270/42

    Abstract: A gas turbine engine includes a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A gear train is defined along an engine axis. The gear train defines a gear reduction ratio of greater than or equal to about 2.3. A fan drive turbine along the engine axis which drives the gear train. The fan drive turbine includes three to six (3-6) stages. A fan is configured for rotation within the fan nacelle for operation at a fan pressure ratio less than about 1.45. A fan variable area nozzle is axially movable relative to said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. A high bypass gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括围绕发动机轴线限定的核心机舱。 风扇机舱至少部分地安装在核心机舱周围，以限定用于风扇旁路气流的风扇旁路气流路径。 齿轮系沿发动机轴线定义。 齿轮系确定齿轮减速比大于或等于约2.3。 沿着发动机轴线的驱动齿轮系的风扇驱动涡轮机。 风扇驱动轮机包括三到六（3-6）个阶段。 风扇被配置为在风扇机舱内旋转，以便在小于约1.45的风扇压力比下操作。 风扇可变区域喷嘴可相对于所述风扇机舱轴向移动，以改变风扇喷嘴出口区域，并且在发动机运行期间调节风扇旁路气流的压力比。 还公开了一种高旁路燃气涡轮发动机。

    REVERSE CORE ENGINE THRUST REVERSER FOR UNDER WING
    25.
    发明申请
    REVERSE CORE ENGINE THRUST REVERSER FOR UNDER WING 有权
    反向核心发动机扭转逆向

    公开(公告)号：US20140252167A1

    公开(公告)日：2014-09-11

    申请号：US14190178

    申请日：2014-02-26

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry

    IPC: F02K1/70 ,  B64D33/04

    CPC classification number: F02K1/70 ,  B64D29/06 ,  B64D33/04 ,  F05D2250/314 ,  Y02T50/671

    Abstract: A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

    Abstract translation: 用于安装在飞行器的机翼下方的燃气涡轮发动机具有在第一轴线上旋转的推进器和包括压缩机部分，燃烧器部分和涡轮部分的发动机核心，其中涡轮机部分更靠近推进器， 压缩机部分。 发动机机芯与空气动力学连接，并具有第二轴。 机舱位于推进器和发动机内核周围。 机舱附着在飞机的机翼上。 机舱的下游端具有至少一个枢转门，其具有致动机构，以使门在收起位置和水平展开位置之间枢转，门中阻止流动以提供逆流。

    REAR MOUNTED REVERSE CORE ENGINE THRUST REVERSER
    26.
    发明申请
    REAR MOUNTED REVERSE CORE ENGINE THRUST REVERSER 有权
    后安装反向核心发动机逆转器

    公开(公告)号：US20140250863A1

    公开(公告)日：2014-09-11

    申请号：US14190171

    申请日：2014-02-26

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry

    IPC: F02K1/62

    CPC classification number: F02K1/60 ,  F05D2210/40 ,  F05D2250/314

    Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

    Abstract translation: 在一个实施例中，用于安装到飞行器机身后部的燃气涡轮发动机具有在第一轴线上旋转的推进器，以及包括压缩机部分，燃烧器部分和涡轮部分的发动机芯，涡轮部分是 比压缩机部分更靠近推进器。 发动机机芯与空气动力学连接，并具有第二轴。 机舱位于推进器和发动机内核周围。 机舱附着在飞机的机翼上。 机舱的下游端具有至少一个枢转门，其具有致动机构，以使门在收起位置和垂直展开位置之间枢转，门中阻止流动以提供逆流。

    LPC FLOWPATH SHAPE WITH GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    27.
    发明申请
    LPC FLOWPATH SHAPE WITH GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 有权
    LPC涡轮形状与气体涡轮发动机轴承轴承配置

    公开(公告)号：US20140248129A1

    公开(公告)日：2014-09-04

    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: F02C3/13

    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。

    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    28.
    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
    30.
    发明申请
    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 审中-公开

    公开(公告)号：US20130312419A1

    公开(公告)日：2013-11-28

    申请号：US13904416

    申请日：2013-05-29

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L Suciu

    IPC: F01D25/16

    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. 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 supporting the shaft relative to the inlet case. The second bearing is arranged radially outward from the shaft.

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