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    REVERSE FLOW SINGLE SPOOL CORE GAS TURBINE ENGINE
    142.
    发明申请
    REVERSE FLOW SINGLE SPOOL CORE GAS TURBINE ENGINE 审中-公开
    反向流动单缸阀芯涡轮发动机

    公开(公告)号：US20160102634A1

    公开(公告)日：2016-04-14

    申请号：US14639164

    申请日：2015-03-05

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Daniel Bernard Kupratis

    IPC: F02K3/04 ,  F02C7/057 ,  F02K1/00 ,  F02C3/06

    CPC classification number: F02K3/04 ,  F01D13/003 ,  F01D13/006 ,  F02C3/06 ,  F02C7/36 ,  F02K1/52 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/314 ,  F05D2260/4031

    Abstract: A bypass housing receives a fan and defines a front end. An airflow path delivers air into an inlet duct over a limited circumferential extent of the bypass housing. An airflow path passes across a low pressure compressor rotor. An airflow path passes through a core engine, which includes a high pressure compressor rotor, a combustor, and a high pressure turbine rotor. Products of combustion downstream of the high pressure turbine rotor pass into an intermediate duct and then across a low pressure turbine rotor. The low pressure turbine rotor is positioned closer to the front end of the engine than is the high pressure turbine rotor. The low pressure turbine rotor is positioned axially intermediate the low pressure compressor rotor and the fan. The low pressure turbine rotor drives both the fan and the low pressure turbine rotor. An aircraft is also disclosed.

    Abstract translation: 旁路外壳接收风扇并限定前端。 气流路径将空气输送到旁路壳体的有限圆周范围内的入口管道中。 气流通过低压压缩机转子。 气流路径通过核心发动机，其包括高压压缩机转子，燃烧器和高压涡轮转子。 高压涡轮转子下游的燃烧产物进入中间管道，然后穿过低压涡轮转子。 低压涡轮转子比高压涡轮转子更靠近发动机前端。 低压涡轮转子轴向位于低压压缩机转子和风扇之间。 低压涡轮转子驱动风扇和低压涡轮转子。 还披露了一架飞机。

    GAS TURBINE ENGINE WITH PAIRED DISTRIBUTED FAN SETS
    143.
    发明申请
    GAS TURBINE ENGINE WITH PAIRED DISTRIBUTED FAN SETS 审中-公开
    燃气涡轮发动机配对分布风扇组

    公开(公告)号：US20150361900A1

    公开(公告)日：2015-12-17

    申请号：US14600101

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02C7/36 ,  F02C3/04

    CPC classification number: F02C7/36 ,  F02C3/10

    Abstract: A gas turbine engine comprises a gas generator rotating along a first axis of rotation, with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine rotates along a second axis of rotation, downstream of at least one gas generator turbine rotor. The fan drive turbine drives a pair of shaft portions extending in opposed directions beyond the axis of rotation of the gas generator.

    Abstract translation: 燃气涡轮发动机包括沿着第一旋转轴线旋转的气体发生器，具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分。 风扇驱动涡轮沿第二旋转轴线旋转，在至少一个气体发生器涡轮机转子的下游。 风扇驱动涡轮驱动一对轴向部分，其延伸超过气体发生器的旋转轴线。

    Two Spool Gas Generator with Improved Air Porting
    144.
    发明申请
    Two Spool Gas Generator with Improved Air Porting 审中-公开
    具有改进空气流通的两个轴流气发生器

    公开(公告)号：US20150337738A1

    公开(公告)日：2015-11-26

    申请号：US14758277

    申请日：2013-05-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord

    IPC: F02C9/18 ,  F02K3/02 ,  F02C7/12

    CPC classification number: F02C7/12 ,  F02C3/13 ,  F02C3/145 ,  F02C6/04 ,  F02C6/08 ,  F02C9/18 ,  F02K3/00 ,  F02K3/02 ,  F05D2220/3217 ,  F05D2220/3218

    Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.

    Abstract translation: 在特征实施例中，燃气涡轮发动机具有由第一涡轮转子驱动的第一压缩机转子和由第二涡轮转子驱动的第二压缩机转子。 第二压缩机转子在第一压缩机转子的上游，第一涡轮转子位于第二涡轮转子的上游。 空气混合系统从第一压缩机转子的上游位置抽出空气，用于输送到环境控制系统。 空气混合系统从第一空气源和第二空气源接收空气。 第一空气源包括在第一压缩机转子的上游的第一压力下的空气。 第二空气源包括较低的第二压力的空气。 至少一个阀控制来自第一和第二源的空气的混合物以实现环境控制系统的预定压力。

    AIRCRAFT WITH FORWARD SWEEPING T-TAIL
    146.
    发明申请
    AIRCRAFT WITH FORWARD SWEEPING T-TAIL 有权
    具有前进的T-TAIL的飞机

    公开(公告)号：US20150298794A1

    公开(公告)日：2015-10-22

    申请号：US14440753

    申请日：2013-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: B64C5/02 ,  B64D41/00

    CPC classification number: B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  B64D33/04 ,  B64D41/00 ,  F02K1/62

    Abstract: An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft portion of the fuselage is angled forward away from the aft portion and out of the discharge of airflow from the thrust reverser.

    Abstract translation: 飞机包括支撑在机身后部的推进器。 靠近推进器支撑推力反向器，用于重定向推进，以降低飞机降落时的速度。 从机身的后部延伸的尾部从后部向前倾斜，并从推力反向器排出气流。

    ANGLED CORE GAS TURBINE ENGINE MOUNTING
    147.
    发明申请
    ANGLED CORE GAS TURBINE ENGINE MOUNTING 有权
    ANGED核心气体涡轮发动机安装

    公开(公告)号：US20150292411A1

    公开(公告)日：2015-10-15

    申请号：US14440698

    申请日：2013-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02C7/20 ,  B64D27/20

    CPC classification number: F02C7/20 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0286 ,  F05D2250/314

    Abstract: A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis. The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative to corresponding ones of the first and second propulsor axes.

    Abstract translation: 用于飞行器的推进系统包括安装在飞行器的机身内的第一和第二涡轮发动机。 第一涡轮发动机包括驱动围绕第一推进轴设置的第一推进器的第一发动机芯。 第二涡轮发动机包括第二发动机芯和围绕平行于第一推进轴的第二推进轴设置的第二推进器。 第一发动机芯和第二发动机芯相对于第一和第二推进器轴线中的相应轴线成一定角度安装。

    Dual Filtration Particle Separator
    149.
    发明申请
    Dual Filtration Particle Separator 有权
    双过滤粒子分离器

    公开(公告)号：US20150292408A1

    公开(公告)日：2015-10-15

    申请号：US14443145

    申请日：2013-06-20

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02C7/052 ,  B01D46/00

    CPC classification number: F02C7/052 ,  B01D46/0023 ,  F02C7/12 ,  F05D2220/327 ,  F05D2260/40311 ,  F05D2260/607 ,  Y02T50/675

    Abstract: A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.

    Abstract translation: 燃气涡轮发动机具有第一颗粒分离器台，其包括用于冲击空气流动通道的外周边处的空气的表面，捕获外周的冲击颗粒，并将捕获的颗粒向第二颗粒分离器台排出。 第一颗粒分离器台的内部空气朝向发动机的核心。 在第二颗粒分离器级上游的清洁空气用于除核心发动机以外的位置的空气功能。 颗粒排放设置在所述第二颗粒分离器台的下游。

    FULL RING SLIDING NACELLE WITH THRUST REVERSER
    150.
    发明申请
    FULL RING SLIDING NACELLE WITH THRUST REVERSER 有权
    全滚动滑扣与扭矩反转

    公开(公告)号：US20150121895A1

    公开(公告)日：2015-05-07

    申请号：US14187027

    申请日：2014-02-21

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  T. David Bomzer

    IPC: F02K1/32 ,  F02C3/04 ,  F02C7/20

    CPC classification number: F02K1/605 ,  F01D25/24 ,  F02C3/04 ,  F02K1/60 ,  F02K1/62 ,  F02K1/625 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F05D2220/32 ,  F05D2230/72 ,  F05D2240/14 ,  F05D2270/051

    Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, 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 is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.

    Abstract translation: 燃气涡轮发动机包括静止的第一环形部分，并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。 燃气涡轮发动机还包括连接到前挂架并沿着后方向从第一环形部分延伸的轨道。 燃气涡轮发动机还包括第二环形部分，其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。 第二环形部分构造成在关闭位置接合第一环形部分，从而提供对发动机芯的通路。 燃气涡轮发动机还包括布置在第二环形部分中的推力反向器。

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